RU2412365C2 - Gas-turbine engine - Google Patents

Abstract

FIELD: engines and pumps.

SUBSTANCE: gas-turbine engine comprises compressor with cooled or with theoretical adiabatic process of compression, device for ignition and combustion of fuel, turbine, device of spent gases heat return into thermodynamic cycle of engine, comprising rotary heat-exchange solid with heat-exchange elements, or with units of heat-exchange elements, comprising heat-exchange surfaces washed with engine working substance, also with working air downstream compressor and spent gases downstream turbine. Heat-exchange device is arranged in the form of spent gases heat recuperator, and its heat-exchange solids are arranged as spaced from each other and are installed both downstream compressor, but upstream turbine, and downstream turbine, or are arranged in the form of heat-exchange unit. Heat-exchange solids of spent gases heat recuperator are arranged as comprising tubes or from elements comprising internal cavities-channels. Internal cavities-channels of heat-exchange elements of heat-exchange solids are filled with intermediate coolant and are included in system of intermediate coolant circulation between rotary heat-exchange elements heated with spent gases downstream turbine and rotary heat-exchange elements, heating working air of engine downstream compressor. Heat-exchange elements are installed in balanced and coaxial or axisymmetric manner in heat-exchange solids with counterflow or with transversely-counterflow, or with counterflow-angular washing of their heat-exchange elements by working substance of engine. Between each other heat-exchange elements are installed with interfacial gaps for washing of their external heat-exchange surfaces by working substance of engine. Heat-exchange elements of heat-exchange solids are arranged as rotary with angular speed providing for quite intensive break-off of working substance elements from their heat-exchange surfaces ("backs"), which are external relative to axis of rotation, and simultaneously providing for quite intensive "discharge" of working substance elements both from side heat-exchange surfaces, and from "bellies" of heat-exchange surfaces.

EFFECT: direct-flow motion of engine working substance via recuperator makes it possible to reduce hydraulic losses, and arrangement of heat-exchange bodies as aerodynamically profiled creates a ventilator effect, which in combination with spent gases heat regeneration makes it possible to increase engine efficiency.

18 cl, 11 dwg

Description

This invention relates to the field of heat engines and, of course, to the field of gas turbine engines of all kinds.

State of the art

Gas turbine engines are known that comprise a compressor with a theoretical adiabatic compression process, a combustion chamber and a turbine with a theoretical adiabatic expansion process, including both uncooled and cooled turbines. See, for example, the book by G.S. Zhiritsky. Aviation gas turbines. Moscow. Publisher of the defense industry. 1950 / L-1 /, Fig. 2,32 on the insert between the pages 62 and 63 and Fig. 2,33 on page 64. See, for example, and L.A. Shubenko-Shubin and others. Gas turbine units. Atlas of designs and schemes. Moscow. Engineering. 1967 / L-2 /, p. 91, figs. 1-252 with GTU of the company Dzheyneral electric, p. 97, figs. 2-2 with GTU-20 of the Leningrad Kirov plant, p. 114, figs. 3-2 from the gas turbine of Kolomenskiy Diesel Locomotive Plant, p. 116, Figs. 3-6 with the gas turbine Metro Vickers, p. 150 from the gas turbine model 6002 from BMW, p. 151, Figs. 4-77 from the gas turbine from Boeing. See, for example, the book by S.A. Vyunov and others, edited by D.V. Chronin. Design and engineering of aircraft gas turbine engines. Moscow. Engineering. 1989 / L-3 /, p. 6, Fig. 1.2, p. 7, Fig. 1.2, p. 8, Fig. 1.3 and Fig. 1.4 with the Pratt-1T9D turbojet circuit Whitney with a high degree of bypass. See, for example, the book of B.A. Ponomarev. Dual-circuit turbojet engines. Oborongiz. Moscow. 1973 / L-4 /, FIG. 1 on the insert at the end of the book with the AI-25 dual-circuit turbojet engine, FIG. 43 on the other inserts of the DTRD RV-211-22 of the Rolls-Royce company.

It is easy to see that in all these gas turbine engines / gas turbine engines /, starting from the 50s of ^the last century and still, already in the 3rd millennium their air-gas paths, including double-circuit DDRDs, including such well-known companies as Dzheyneral-Electric, Rolls-Royce, Pratt-Whitney, as well as Russian NPOs Saturn and UMPO, are executed according to the simplest thermodynamic cycle from the number of theoretical thermodynamic cycles that have long been known in thermodynamics, and therefore, to the least effective of the long-known ones. For, as it is easy to see, the air-gas paths of all these gas turbine engines, including double-circuit diesel engines, have a compressor with a theoretical adiabatic compression process that has the greatest compression work and minimizes the useful work of the turbine, and a turbine with a theoretical adiabatic expansion process that has the opposite the smallest work of expansion, as well as due to the absence in their thermodynamic cycles of the process of returning heat from exhaust gases, which leads to sufficiently large losses of thermal energy from exhaust gas mi leaving the engine.

All this applies to internal combustion engines / internal combustion engines /, which in most cases have a theoretical adiabatic compression process and the complete absence of heat recovery of exhaust gases.

And although in the aforementioned gas turbine engines the thermal efficiency is determined by the expression

, где

,

where

,

grows quite intensively with increasing gas temperature in front of the T ₃ turbine with respect to the ambient temperature T ₁ , see, for example, the book by J.I. Schnee. Gas turbines. Moscow. Mashgiz. 1960 / L-5 /, pp. 20-22. Undoubtedly, it should be noted that the performance of cooled turbines has increased in the gas turbine engine and, accordingly, the gas temperatures in front of the turbine have substantially increased, and the thermal efficiency of the gas turbine engine has accordingly increased. However, with an increase in the temperature of the gases in front of the turbine, the optimal degree of increase in pressure also intensifies. See, for example, Table 3 in / L-5 / on page 32. And for example, in accordance with L-4 on pages 82-83 in the DDRD model 1T9D of the Pratt-Whitney company of the Boeing-747 aircraft, its compressor has 3 low pressure stages and 11 high pressure stages. And its high pressure turbine has 2 stages, and its low pressure turbine has 4 stages. And accordingly, the GTE multi-wheel rotor turned out to be not only very expensive, but also very long and heavy. The engine casing also became long, and thick-walled, and heavy, including due to the high internal pressure in it. And in general, the engine is undoubtedly very expensive, long, heavy, and efficiency is very far from excellent. For the compression work taken away by the compressor from the turbine has significantly increased. And therefore, consumers are not very interested in high thermal efficiency, since it does not say anything about what remains in the turbine for useful work. Undoubtedly, consumers are more interested in internal efficiency, which is already determined by the difference between the available turbine and compressor operations. For the internal efficiency is determined by the expression

in L-5 on page 23, where Q ₁ is the amount of supplied thermal energy, taking into account losses in the combustion chamber,

η _ks , η _t and η _k - efficiency of the combustion chamber, turbine and compressor,

q _t - the amount of fuel supplied to the combustion chamber per 1 kg of air.

And according to L-5 on page 21, even

и

and

in the aforementioned gas turbine engines, the theoretical internal efficiency is only 0.346. And even with ∑ = 5.40 and the corresponding φ _opt. = 30 their theoretical internal efficiency can be equal to 0.444. Whereas the theoretical internal efficiency of a gas turbine engine even with a one-stage theoretical adiabatic compression process and the same expansion process and ∑ = T ₃ / T ₁ = 4.31, but already having exhaust gas heat recovery sufficiently close to ideal, may already be equal to 0, 55-0.60. See, for example, the graphs of the internal efficiency of a gas turbine engine in Figs. 55 and 56 and L-5 on page 70.

Of course, the internal efficiency of a gas turbine engine is not yet an efficient efficiency, because it has not yet taken into account mechanical losses in bearings, the drive of fuel and oil pumps, and other expenses for own needs. And according to L-5 on page 89, the effective efficiency of a gas turbine engine is determined by the expression

где

Where

η _mt and η _mk are respectively the mechanical efficiency of the turbine and compressor,

Δh _hydr. - differential equivalent to hydraulic resistances, η _кс - efficiency of the combustion chamber.

And according to L-5 on page 89, the theoretical effective efficiency can be less than the theoretical internal efficiency by only 1 ÷ 2% of the installed capacity. However, in reality, these losses can be significantly large. And given that mechanical losses, including in bearings, and on the pump drive, are relatively small, and the fact that the subject of the invention is a significant reduction in the total hydraulic losses and heat losses to a relatively small level, and also considering that L-5 presents graphs that make it possible to judge the perfection of theoretical thermodynamic cycles among themselves, as well as being a guideline, to which the efficiency of GTEs with one or another theoretical thermodynamics can be approximated ical cycle, we will use them in the future for a relative assessment of known engines relative to each other.

And undoubtedly, taking into account the above, G.S. Zhiritsky, even in his 1950 book L-1 of issue on page 37, set the task of creating a gas turbine engine with heat recovery of exhaust gases, which is structurally and schematically presented in Fig. 2.34 on page 37 65, and in the second stage he considered it necessary to proceed to the creation of a gas turbine engine with a cooled compression process to reduce the compression work and heat recovery of the exhaust gases to return the heat of the exhaust gases to the thermodynamic cycle.

And undoubtedly, in accordance with this, gas turbine engines have become known, which contain a compressor with a theoretical adiabatic compression process, a combustion chamber, a turbine with a theoretical adiabatic expansion process and an exhaust gas heat recovery device in the form of a regenerator. See, for example, the Chrysler A-831 engine in FIGS. 4-90 and FIGS. 4-91 in L-2 on page 153 with a rotating heat exchanger with a diameter of 458 mm and a radial depth of 76 mm for air in it. However, its efficiency turned out to be even slightly worse than that of the gasoline carburetor ICE of the Moskvich 412 car. For according to the technical characteristics, the automobile AGTD A-831 in L-2 on page 153 has the lowest specific fuel consumption of 231 g / lsch, whereas according to, for example, book L.I. Belkin and others. Car Moskvich 412. Moscow. Engineering. 1971, / L-6 /, p. 9, the minimum specific fuel consumption of a Moskvich 412 automobile is 225 g / lsch. And according to the book of M.O. Vysotsky and others. Car MAZ 500 and its modifications. Moscow. Engineering. 1968 / L-7 /, p. 16, the minimum specific fuel consumption of the YaMZ-236 diesel engine is only 175 g / lsch << 231 g / lsch. Those. The Chrysler AGTD 1-831 created by its efficiency turned out to be worse than even a carburetor ICE with spark ignition, and even worse than a diesel ICE with the simplest thermodynamic cycle, although it may not be completely correct to compare them, because the maximum temperatures of ICE cycles are spark ignition is 2500-2800 K, and for diesel engines 1800-2200 K. See, for example, a book by V.M. Arkhangelsky and others. Car engines. Moscow. Engineering. 1977 / L-8 /, p. 45. However, no one prevented Chrysler from creating an AGTD with a higher gas temperature in front of the turbine. Secondly, from the AGTD scheme A-831 b / L-2 / on page 153 and Figs. 4-91, it is seen that the temperature of the gases in front of the regenerator is 647 ° C, and after it 260 ° C, which corresponds to the thermal difference "triggered "in the regenerator 387 ° C, although the temperature of the working air in front of the regenerator is 218 ° C. As a result, there is a lost temperature drop with exhaust gases of 42 ° C. 42 ° С, this is undoubtedly a significant loss of thermal energy with exhaust gases so that regeneration can be considered close to ideal, and the thermodynamic cycle AHTD A-831 close to theoretical. Far from an ideal regenerator, it turned out also because with a diameter of the heat-exchange body of the regenerator of 458 mm and a depth of its passages-channels of 76 mm for movement in them and compressed working air, this undoubtedly leads to sufficiently large losses of compressed working air into the cavity with exhaust gases the movement in these channels of compressed working air as a result of rotation of the heat exchange body between the cavities with compressed working air and exhaust gases. Undoubtedly, there are losses of compressed working air in the regenerator seals as well. Undoubtedly, there are significant hydraulic losses in the air-gas path of the gas turbine engine due to its unobtrusiveness, and even more so with repeated and rather sharp turns, as well as due to the increase in the air-gas path by this, as well as due to undoubted losses / hydraulic / flow of the working fluid in the heat exchange body of the regenerator.

Aircraft gas turbine engines are also known that comprise a compressor with a theoretical adiabatic compression process, a combustion chamber, a turbine with a theoretical adiabatic expansion process, and an exhaust gas heat recovery device in the form of a regenerator. See, for example, the book by G.S. Skubachevsky. Aircraft gas turbine engines. Design and calculation of parts. Moscow. Engineering. 1974 / L-9 /, p. 13, Fig. 1.09. And as stated in L-9 on page 14, "Regenerators for the recovery of exhaust gas heat and for heating the incoming air into the engine are rarely used, since they have a large mass and low operational reliability."

Gas turbine engines are also known, which comprise a compressor with a stepwise compression process and with intermediate cooling of the compressed air, a combustion chamber, a turbine with a theoretical adiabatic expansion process, and a device for recovering heat from exhaust gases in the form of a recuperator. See, for example, L-2, FIGS. 2-6, p. 98 with the ship GTU RM 60 company Rolls-Royce. However, despite the fact that Rolls-Royce created its own gas turbine with an even more advanced thermodynamic cycle, which also includes a cooled process of compressing the working air in addition to the heat recovery process of the exhaust gases, their gas turbine PM 60 turned out to be even more voracious than the A-831 gas turbine engine Chrysler company. For according to the technical characteristics of the GTU RM 60 in L-2 on page 98, it has an efficiency of only 21.2%, and the specific fuel consumption is 295 g / lsch. And undoubtedly, this is the case for the following reasons. For, firstly, as can be seen from FIGS. 2-5 in L-2 on page 98, the temperature of the gases in front of the exhaust gas heat recovery unit is 327 ° C, and after it - 263 ° C. Those. in the recuperator, only the temperature difference of 62 ° C is utilized, and the compressed air temperature in front of the recuperator is 151 ° C, the lost temperature difference is 92 ° C> 62 ° C. It is easy to notice that this recuperator is far enough from ideal. And moreover, as the author believes, there is more harm than good from this recuperator. For the designers of the Rolls-Royce company for the regeneration of the entire 62-degree thermal difference came up with the idea of driving working air back and forth along very long air ducts with numerous turns, including in rather bent pipes in the heat exchanger itself. And undoubtedly, this technical solution led to quite significant hydraulic losses in comparison with a gas turbine engine with a straight-through flow of a working fluid through the gas-turbine part. And in accordance with L-5 on pages 74-89, undoubtedly insufficiently efficient heat recovery of exhaust gases and undoubtedly significant hydraulic losses in the gas-turbine engine gas duct, as well as the very low temperature of the gases in front of the turbine at 827 ° C did not allow the company, Rolls-Royce get at least acceptable efficiency in their PM 60 gas turbine engine.

Gas turbine engines are also known with even more advanced theoretical thermodynamic cycles containing a compressor with a stepwise compression process and intermediate cooling, a combustion chamber, a turbine with a stepwise expansion process and intermediate heating, as well as an exhaust gas heat recovery device in the form of a recuperator. See, for example, the Ford Model 704 gas turbine engine in Figs. 4-81 and Figs. 4-82 in L-2 on page 152 and the Ford 705 gas turbine engine in the German ATZ magazine Automobiltechnieche Zeitschrift.

Automotive industry No. 11, 1967 / L-10 /, p. 393-396, including FIG. 51 on page 393, and FIGS. 52 and 53 on page 394, and FIG. 65 on page 396 with the schedule of specific fuel consumption from the minimum of 179 g / lsch to 196 g / lsch at maximum power. It is easy to see that the fuel economy and AGTD Ford 705 with an even more perfect thermodynamic cycle turned out to be slightly worse than that of a simple YaMZ-236 diesel engine with the simplest thermodynamic cycle, which, as noted above, has a minimum specific fuel consumption of 175 g / lsch. Whereas according to schedule No. 5 in FIG. 56 to L-5 on page 70, the internal efficiency of a gas turbine engine at ∑ = T ₃ / T ₁ = 4.31 could be at the level of 0.55-0.60, if it were implemented close enough to theoretical.

But, firstly, according to FIG. 51, on page 393 in L-10, the flow part of the AGTD Ford 705 is not direct-flow, but with repeated and rather sharply curved turns of the working fluid flow and has a correspondingly much longer air-gas path if he was direct-flow. This undoubtedly led to significant hydraulic losses and a corresponding decrease in internal and effective efficiency. Additional hydraulic losses are created by heat exchangers, including an intermediate cooler of compressible air, and an exhaust gas heat recovery unit, as well as a non-direct-flow combustion chamber. This also reduces internal and efficient efficiency.

Secondly, the regeneration of heat from exhaust gases is far from ideal. For according to FIG. 51 in L-10 on page 393, the temperature of the gases in front of the recuperator is 582 ° C, and after it - 395 ° C, while the temperature of the compressed air in front of the recuperator is 330 ° C. As a result, there is a lost thermal drop with exhaust gases of 65 ° C with a "triggered" thermal drop in the recuperator 187 ° C. Far enough from the ideal and intermediate cooler compressible air. For the temperature of the compressed working air after the intercooler is 106 ° C, while the ambient temperature is 38 ° C. The theoretical undercooling is 68 ° C, which led to an increase in the compression work in comparison with the theoretical, and, accordingly, to a decrease in the useful work of the turbine.

Thirdly, the temperature of the gases in front of the turbine is 927 ° С, which corresponds to ∑ = Т ₃ / Т ₁ = 3.86 <4.31. At that time, as already noted above, the maximum cycle temperatures in diesel ICEs are 1800-2200 K, and in ICEs with spark ignition 2500-2800 K. But ICEs have quite effective cooling systems for this.

Gas turbine engines are also known, which include a compressor with a theoretical adiabatic compression process, a combustion chamber, a turbine with a theoretical adiabatic expansion process made of ceramic, and an exhaust gas heat recovery device made in the form of a regenerator with a ceramic heat exchange body. And, as some media claim, such gas turbine engines can operate at gas temperatures in front of the turbine up to 1250 ° C. See, for example, Automobil Magazine No. 12, 1981, Czechoslovakia / L-11 /, pp. 25-27. And this magazine also includes the Mercedes-Benz gas turbine engine created as an experimental for the Aito-2000 car along with diesel and gasoline variants. And as it turned out, the fuel efficiency of the ATO-Aito-2000 is already slightly better than that of its diesel counterpart. And with the speed of the Aito 2000 car 90 km / h, the fuel consumption is 5.5 liters, and its diesel counterpart 5.7 liters. See, for example, an article from the Bulgarian newspaper Avtomotosvyat / AMC / №12 ^80's called "Mineralokeramikata - Gas Turbine". / L-12 /. However, it is undoubted that the thermodynamic cycle implemented in AGTD Aito-2000 with a ceramic uncooled turbine and with an exhaust gas heat generator is still not equivalent to a theoretical thermodynamic cycle with theoretical thermodynamic adiabatic compression and expansion processes and regeneration of exhaust gas heat, and secondly, because the gas-gas path of the AHTD Aito-2000 is not direct-flow and has repeated and rather sharply curved turns of the flow of the working fluid when it moves with enough sokimi speeds. Secondly, here the length of the air-gas tract has increased significantly. Thirdly, there are hydraulic losses during the movement of the working fluid through the regenerator. Fourth, the output edges of the blades of the ceramic turbine wheel have thicker edges, leading to an increase in hydraulic losses when they flow around the working fluid. Fifthly, the combustion chamber is also not direct-flow. Sixthly, there are undoubtedly significant losses of compressed working air in rather long and very numerous channels of the rotating heat-exchange body of the processed gas heat regenerator when they are moved from the high-pressure cavity to the low-pressure cavity with exhaust gases. Seventh, despite the lack of information on the temperatures of the exhaust gas before and after the regenerator and on the temperature of the compressed working air in front of the regenerator, there is undoubtedly a significant lost temperature difference with the exhaust gases into the atmosphere. And therefore, AGTD Aito-2000 is still quite far from the theoretically possible efficiency.

Gas turbine engines are also known, which include a compressor with a theoretical adiabatic compression process, a combustion chamber and a turbine with a theoretical adiabatic expansion process and with sufficiently effective air cooling, including turbine wheel blades. See, for example, an article by a doctor of technical sciences N.G. Olkhovsky from VTI "Development of promising energy gas turbines" from the journal "Heat Power" No. 4, 1996 / L-13 /, pp. 66-74. And according to L-13 in Siemens GTU with an air-cooled turbine, the gas temperature in front of the turbine is 1310 ° C. And at φ = 16.6 efficiency GTU 38%. It is without regeneration. See table 1 in L-13 on page 66. In particular, according to L-13 on page 68, the working blades of the first and second stages of the turbine are made single-crystal.

, - наихудший в ГТД с простейшим термодинамическим циклом. Смотрите, например, стр.28 в Л-5, гдеAnd in a Westinghouse gas turbine with an air-cooled turbine, the temperature of the gases in front of the turbine is already 1410 ° C. And already at φ = 19.2, the efficiency of a gas turbine without regeneration is 38.5%. See, for example, table 1 in L-13 on page 66. It is easy to see that even at sufficiently high gas temperatures in front of the turbine the efficiency of such gas turbine engines with the simplest thermodynamic cycle, i.e. not even having heat recovery from exhaust gases, is still small. For a coefficient expressing the ratio of the power developed by the turbine to the power taken from it by the compressor, determined by the expression

, - the worst in a gas turbine engine with the simplest thermodynamic cycle. See, for example, p. 28 in L-5, where

N _t - turbine power,

N _to - compressor power,

η _t and η _k are respectively the efficiency of the turbine and compressor, and also see the graphs of the changes in λ _in Figs. 59 and 60 in L-5 on page 72. In this connection, some world-famous companies, including Siemens and Westinghouse, used a complex containing a steam generator and a steam turbine instead of regenerators or heat exchangers for exhaust gas heat. The steam generator takes away the heat of the exhaust gases, and the steam turbine turns it into work, including useful work. As a result, the efficiency of their combined cycle plants / CCGT / increased to 58%. See, for example, table 1 in L-13 on page 66. This clearly confirms that even gas turbine engines with theoretical adiabatic processes of compression and expansion, but having heat recovery of exhaust gases close to ideal, can have an efficiency of about 58%. And therefore, it makes direct sense to create a gas turbine engine with heat recovery from exhaust gases. For ISUs are acceptable only for stationary power plants, but for vehicles they are undoubtedly both bulky and heavy.

SUMMARY OF THE INVENTION

1. A gas turbine engine containing a compressor with a cooled compression process or with a theoretical adiabatic compression process, a device or device for igniting and burning fuel, a turbine cooled or uncooled, with a heated expansion process or with a theoretical adiabatic expansion process, a device or a device for heat recovery gases into the thermodynamic cycle of the engine, containing either a rotating heat-exchange body or rotating heat-exchange bodies heat-exchange elements or with blocks of heat-exchange elements containing heat-exchange surfaces washed by the engine’s working fluid, including working air after the compressor and exhaust gases after the turbine, characterized in that its heat-exchange device or exhaust gas heat recovery device is made or made in the form of a heat recuperator exhaust gases, and its heat-exchange bodies are made spaced from each other and installed after the compressor, but before the turbine, and after the turbine, or They are not spaced on before and after the turbine, but, for example, are made in the form of a heat exchange unit, and the heat exchange bodies of the exhaust gas heat recovery unit themselves are made containing tubes, including, perhaps, not only round ones, or made containing elements of a tubular type, or from elements containing internal cavity-channels, and internal cavity-channels of heat-exchange elements of heat-exchange bodies are filled with an intermediate heat carrier and included in the circulation system of the intermediate heat carrier between rotating heat heat exchanged elements heated by exhaust gases after the turbine and rotating heat exchange elements heating the engine working air after the compressor, and heat exchange elements are balanced and coaxially or axisymmetrically installed in heat exchange bodies with countercurrent or with transverse countercurrent or countercurrent-angular washing of their heat exchanger elements with working the engine body, and between them tubular heat-exchange elements or heat-exchange elements of the tubular type are installed with annular gaps, whether more with inter-surface gaps for heat-exchange elements containing internal cavity channels for washing their external heat-exchange surfaces with a working fluid of the engine, including for the movement of the working fluid between them with radial components of its movement, the heat-exchange elements of the heat-exchanging bodies being rotated at an angular speed, providing a sufficiently intense separation from their external with respect to the axis of rotation of the heat exchange surfaces / "backs" /, colliding with them and, accordingly, heat exchange the elements of the working fluid that are connected with them, and at the same time provide a sufficiently intense “discharge” of the working fluid elements from both the lateral heat-exchange surfaces and the “belly” of the heat-exchange surfaces that touch the heat-exchange surfaces and, accordingly, heat-exchange with them at the same time as they are sucked .

2. The invention consists in the fact that in a gas turbine engine according to claim 1, the heat-exchange bodies of its exhaust gas heat recuperator are preferably installed along the one-way travel of the working fluid of the engine from the entrance to the gas turbine engine to its exit from the gas turbine engine, including after the compressor, and after the turbine, including either coaxial to the axis of rotation of the turbine and the axis of rotation of the compressor, and including, for example, made rotating relative to the axis of rotation of the turbine and compressor, and including rotating at speeds different from the speed of rotation of the turbine and of the compressor or heat exchange bodies can also be made installed on the one-way travel of the working fluid from its entrance to its exit from the gas turbine engine and after the compressor, and after the turbine, and around the rotation axes of the turbine and compressor, but are made, for example, rotating and not coaxial to the axes rotation of the turbine and compressor, either made installed and not around the axis of rotation of the turbine and compressor, and rotating around its own axis of rotation.

3. The essence of the invention lies in the fact that the gas turbine engine according to claim 1 is characterized in that the heat exchange elements of the heat exchange bodies of its exhaust gas heat exchanger are preferably balanced and coaxially or axisymmetrically installed in its heat exchange bodies and are preferably made in the form of twisted tubular coils of different diameters and preferably installed one in the other, and the other in the next, etc., including twisted tubular coils can be made and 2 coils of the same diameter with respectively longitudinally stretched and coils and nested like one another with successive turns of one coil interleaved with the turns of the other coil, i.e. as if made in the form of two-way coils, and can also be made in the form of three-way and more inlet coils, and can also be made in the form of spiral wound pipes with turns laid one next to the other in radial tube layers with side gaps between the pipe coils, including those laid in pipe coils and pipe coils, including those with radial clearances between the pipe coils, or heat exchange elements made in the form of multilayer pipe sets, wound along a helical line, including those that make up a part of the turn, either made in the form of straight axis-longitudinal pipes, balanced and preferably axisymmetrically installed in heat-exchange bodies, or in the form of radially mounted pipes installed on the periphery of heat-exchange bodies, made, for example, of different lengths from the periphery of the heat exchange bodies as the circular cross-sectional area of the heat exchange body decreases as it approaches the axis of the heat exchange body, and also, for example, in the form of straight radial tubes, or in the form of radial branching pipes of the snowflake type, either in the form of spirally wound tubular coils, or elements containing tubular type elements, and heat-exchange elements, including tubular ones, or from tubular type elements, are preferably made loose between themselves, including in the longitudinal-axial directions, including in the radial layers, if any, as well as in the radial directions, including between the radial layers, if any, and also preferably attached to the supporting elements of the heat exchange bodies supporting-spacer elements, including aerodynamically profiled ones with optimal flow around them with the engine working fluid, including those made taking into account the angular speeds of rotation of the heat-exchange elements, their radii of rotation and the speed of movement of the working medium through heat-exchanging bodies, including taking into account adopted countercurrent, or transverse countercurrent, or countercurrent-angular flow around the working fluid of the heat exchange elements, and the input and output sections of the support-spacer and guide elements prefer It made no difference to their input and output angles providing forced motion of the working fluid through the heat exchange body.

4. The essence of the invention lies in the fact that in the gas turbine engine according to claim 3, the supporting-spacer and guiding elements of the heat-exchanging bodies are made, for example, in the form of aerodynamically profiled combs, preferably made with at least mounting connectors along the axes of the beds in them under heat-exchange elements, including, if necessary, contain elastic support-spacer elements, including, if necessary, and adjustable, including preferably short-circuited in the heated working state of the heat-exchanging bodies.

5. The essence of the invention lies in the fact that in the gas turbine engine according to claim 1, the inner diameters of the tubes of the heat exchange elements are preferably made with relatively small sizes, up to the minimum conditions for a sufficiently effective circulation of an intermediate heat carrier in them, including the conditions for the efficiency of its heat transfer with inner walls.

6. The essence of the invention lies in the fact that in a gas turbine engine according to claim 1, the axis of the internal cavity-channels of the heat-exchange elements, including the axis of the tubes of the heat-exchange elements, then simply the internal cavity-channels of the heat-exchange elements, starting from the inlets to the heat-exchange elements to the outlet openings from the heat exchange elements are preferably mounted relative to the axes of their rotation with a relatively small radial-axial slope, bearing in mind that the heat carrier located in the heat exchange elements is in a centrifugal field x forces and changes its temperature and accordingly its density in the direction of its movement in them, or the axis of the cavity-channels of the heat exchange elements are made without radial slope, and the axis of the outlet holes from the internal cavity-channels of the heat exchange elements installed after the compressor are preferably mounted on such the same radial distances from the axes of their rotation, as the axis of the circulating pipelines connected to them by either channels or channels, as well as the axes of the inlet openings of the cavity-channels of the heat exchange elements in, installed after the turbine, respectively, the axis of the outlet openings of the cavity-channels of the heat exchange elements installed after the turbine, are preferably located at the same radial distances from the axes of their rotation as the axes of the pipelines connected to them, or channels, or channels, inlets cavities-channels of heat-exchange elements installed after the compressor, or at radial distances from the axes of their rotation, sufficiently close to the same, and the intermediate heat circulation system the carrier preferably selectively connects the outlet openings from the cavity-channels of the heat-exchange elements installed after the compressor with the inlet openings of the cavity-channels of the heat-exchange elements installed after the turbine and preferably located at equal radial distances from the axes of their rotation, or close enough to the same, and preferably similarly interconnected by circulation pipes of the intermediate coolant outlet openings from the cavity-channels of the heat belt elements installed after the turbine, with inlet holes of the cavity channels of the heat exchange elements installed after the compressor.

7. The invention also consists in the fact that in a gas turbine engine according to claim 6, the intermediate coolant circulation system preferably contains circulation devices in each circulation loop, or contains an integral circulation device, either without it, or a non-selective intermediate coolant circulation system, and preferably each circuit of the intermediate fluid between the heat exchange elements of the heat transfer bodies, or a single circuit of the intermediate fluid between the heat exchange bodies and preferably comprise cavities or an expansion cavity of the intermediate heat carrier, made, for example, in the form of tubes or channels docked with them or channels with a slight deviation of the axes of their channel-cavities from the axial lines of the circumferences of the internal cavity-channel of the heat-exchange elements to the side to the axis of rotation, and the expansion cavity and the supply of intermediate coolant, in turn, is preferably connected by pipelines or channels, or channels, or directly with individual or group and gas-vapor expanders, or with an expansion gas-vapor medium, preferably made in the form of bellows, or in the form of expansion devices of a different type, including, for example, in the form of a device containing a gas-vapor receiver of an excess volume of a gas-vapor medium, a compressor for pumping an excess volume of a gas-vapor medium in receiver from expansion cavities and intermediate coolant reserve, including via preferably contained intermediate cooler, non-return valve between compressor and receiver, pressure switch in the expansion cavity and the reserve of the intermediate coolant for turning on and off the compressor, steam-gas reducers or the reducer for returning the vapor-gas medium from the receiver into the expansion cavity and the reserve of the intermediate coolant or into the expansion cavity and the reserve of the intermediate coolant after the volume or volumes of the media decreases there as the intermediate coolant cools , for example, after stopping a gas turbine engine.

8. The invention also consists in the fact that in a gas turbine engine according to claim 1, tubes of heat exchange elements of a heat exchange body or heat exchange bodies installed or installed after a compressor and preferably containing turbulent pulsations of an intermediate heat carrier in them are preferably made with a larger “back” thickness than abdomen.

9. The invention also consists in the fact that in a gas turbine engine according to claim 1, the elements of the intermediate heat-carrier circulation system between the heat-exchange elements of its heat-exchange bodies are preferably located at radial distances from the axis or from the axes of their rotation, not less than the radial distances from the axis or from rotation axes of the internal cavity-channels of the heat-exchange elements connected by them.

10. The essence of the invention lies in the fact that in a gas turbine engine according to claim 1, comprising a compressor, a turbine and rotating heat exchange bodies of its exhaust gas heat exchanger, its heat exchange bodies are preferably mounted through support-force elements on bearings, preferably mounted on the necks of axial-longitudinal bearings GTE, preferably made around the shafts of the turbine and compressor, or around the shaft of the turbine and compressor and preferably coaxially with them, including those made, for example, on the transverse partitions of the GTE housing, and the axes of these axial longitudinal bearings are preferably provided with longitudinal longitudinal cavities for passage of turbine and compressor shafts or turbine and compressor shafts, and the radial axial bore cavities for bearings of turbine and compressor shafts or turbine and compressor shaft or bed bores for bearings of turbine and compressor shafts or turbine and compressor shafts are made in end caps-cases of standard longitudinal supports, or bed bores for Ipnikov of the turbine and compressor shafts or turbine and compressor shafts are made in cup housings mounted, for example, on horizontal longitudinal supports from the side of their inner ends after bearings of heat-exchanging bodies, counting from the transverse partitions of the turbine engine housing, including, if necessary, cup housings made with large diametrical dimensions of the bores for the bearings of the turbine and compressor shafts or of the turbine and compressor shafts than the diameters of the support journals for the bearings of heat exchangers on the longitudinal longitudinal bearings, and the transverse partitions of the casing of the gas turbine engine are preferably made containing central parts, including those containing axial longitudinal supports and peripheral parts attached to the casing of the gas turbine engine, as well as containing annular passages between them, i.e. between the central and peripheral parts for movement of the working fluid of the engine through them, and between themselves the central and peripheral parts of the transverse partitions of the casing of the gas turbine engine are preferably connected by aerodynamically profiled support-force elements, or the transverse partitions of the casing of the gas turbine engine are made without peripheral parts with the fastening of the support-force elements, for example, to the casing of the gas turbine engine, and the turbine of the gas turbine engine is preferably made comprising an inner casing with preferably fixed elements fixed to it mi of the turbine flow section, and the turbine’s inner case itself is preferably fixed through preferably aerodynamically profiled support-force elements to preferably the same axial longitudinal bearings as the heat exchange body bearings, including preferably after the heat exchange body bearings, counting from the transverse partitions of the turbine engine body, or the turbine’s inner casing is fixed to the end caps of the axial longitudinal supports, or to the existing end cover on some axial longitudinal support, if they are either present or The turbine’s axial housing is mounted on the housing-cups of the shaft bearings on the axial longitudinal bearings, or on the housing-glass of any of the longitudinal longitudinal supports, if either it is on the longitudinal longitudinal supports or fixed in mutual combination between them, as well as any of the bearings the shafts of the turbine and compressor, or any of the bearings of the shaft of the turbine and compressor, are installed in the bore-beds of the housings or in the housing, made, for example, resting on the inner turbine housing or on the supporting elements of the inner housing turbine.

11. The essence of the invention lies in the fact that in a gas turbine engine according to claim 10, the support-force elements of its heat-exchanging bodies are preferably made based on bearings through rotating bearing housings and preferably contain limited heat-conducting elements, and are also preferably thermally compensated or containing thermal compensation devices .

12. The essence of the invention lies in the fact that in the gas turbine engine according to claim 11, the heat-compensating devices of the support-strength elements of its heat-exchange bodies are made, for example, containing at least three double-hinged levers on each of the supports of the heat-exchange bodies not lying in the same plane, or containing 4 double-hinged levers or more, including preferably containing supporting-limiting elements of ultimate deformations, including preferably adjustable.

13. The essence of the invention lies in the fact that in the gas turbine engine according to claim 11, the thermally compensated supporting-force elements of its heat-exchanging bodies are made, for example, containing elastically deformable elements, including preferably containing supporting-limiting elements of ultimate deformations, including preferably adjustable.

14. The essence of the invention lies in the fact that in the gas turbine engine according to claim 11, the rotating support bearing housings of the support-force elements of its heat exchange bodies are preferably made cooled.

15. The essence of the invention lies in the fact that in a gas turbine engine according to claim 1, heat-exchange bodies or blocks of heat-exchange bodies of its exhaust gas heat recuperator, installed both after the compressor and after the turbine and rotate preferably on bearings coaxially to the axes of rotation of the turbine and compressor, are preferably connected between themselves, preferably balanced and preferably coaxial or axisymmetric connecting element, or elements, and in the zone of the turbine located or located around the periphery of the turbine, and preferably tionary containing or containing channels for circulating a coolant circulating intermediate tube.

16. The invention consists in the fact that the gas turbine engine according to claim 1 contains a mechanism for the forced rotation of heat-exchange bodies.

17. The essence of the invention lies in the fact that the TBG according to claim 1 preferably contains a device or device for automatic balancing of the rotor of the recuperator, including those containing or containing balancing bodies-weights mounted on the rotor of the recuperator, actuators that move the balancing bodies-weights, as well as tracking devices of increased centrifugal forces on the rotor of the recuperator in any or in any of the radial directions in comparison with the others, for example strain gauge devices, connected, for example, on supporting-power elements of heat-exchanging bodies, and strain gauge devices are included, for example, in the electrical circuit of the control apparatus or in the electrical circuits of control apparatuses for actuators, including those containing or containing, for example, elements of electric bridge circuits .

18. The essence is that in the gas turbine engine according to claim 17, the automatic balancing device of its recuperator rotor is made, for example, containing actuators rotating on the axes, for example, eccentrically located balancing bodies-weights, or is made, for example, containing rotary actuators and moved in radial or in radially containing directions, for example, on threads, for example, thread-containing balancing cargo bodies.

The list of submitted drawings

FIG. 1 is a longitudinal axial section of a gas turbine engine.

FIGURE 2 is a heat recovery exhaust gas assembly, heat transfer elements are not conventionally shown.

FIG. 3 is a section along aa of FIG. 2.

FIGURE 4 - embodiment of the front integrated engine mount / compressor side /.

FIG.5 is another option for the front integrated engine mount / compressor side /.

FIG.6 is a longitudinal-axial section of a variant of the drive mechanism of the rotor of the exhaust heat recuperator.

FIG. 7 is a longitudinal axial section through an embodiment of a heat exchange body of an exhaust gas heat recuperator.

FIG. 8 is a sectional view of a heat exchange body according to BB of FIG. 7 and view B of FIG. 7.

FIG. 9 is a view D of FIG. 7 and views D and E of a view G.

FIG.10 is a variant of the hydraulic circuit of the intermediate fluid circulation.

FIGURE 11 is a section of a demonstration device of high efficiency of the heat transfer method according to the patent of the Russian Federation No. 2130156.

Gas turbine engine

One of the possible variants of the proposed gas turbine engine in axial longitudinal section is shown in figure 1. It preferably has an outer casing 1, made, for example, in the form of a pipe, and has flanges on both sides. The housing can be either in the form of a conical transition, or in the form of a combination of pipes and a conical transition, or in the form of a tubular frame with flanges. The housing may have hatches and removable or opening covers for assembly, disassembly, adjustment, control. On the flanges of the housing 1 on the landing centering belts are installed on both sides the cover-housing 2 and the cover-housing 3 and are attached to the flanges of the housing with bolts or studs with nuts. For example, an angular contact bearing 4 of the shaft 5 of the compressor 6 is installed in the outer center-bore in the housing-cap 2. The bearing can be made in the form of a block of 2 ^x angular contact bearings, either in the form of a block of persistent and radial bearings, or radial bearings. The bearing 4 is mounted and secured to the shaft 5, for example, by a sleeve 7, mounted “on a hot” and preferably in a circular polished groove on a shaft with a depth of, for example, several microns with smooth polished radius transitions. The bearing 4 in the cover housing 2 is closed, for example, by a cover 8, mounted on the cover housing 2, for example, by bolts. The output of the shaft 5 from the cover 8 is preferably sealed, for example, with a complex non-contact seal, containing, for example, a centrifugal conical oil-saving disk and an oil protection sleeve with a shoulder on the free end, made on the cover from its inner side around the outlet in the cover for the shaft 5, such as for example, in the book of Yu.M. Nikitin. Designing elements of parts and components of aircraft engines. Engineering. Moscow. 1968 / L-14 /, p. 187. The shaft seal 5 in the opening of the cover 8 preferably also contains a labyrinth-breather seal, not shown in FIG. 1, for example, shown, for example, in FIG. 5.71 in L-14 on page 180, including between the neck of the shaft 5 and the inner the surface of the oil shielding sleeve on the cover 8, as well as, for example, between the outer end surface of the cover 8 around its outlet and the flange of the shaft 5 for mounting the compressor wheel 6. The internal support bearing 9 of the compressor shaft is worn on the shaft, for example, in a sliding fit, but is preferable use op a cylindrical cylindrical bearing for axial thermal extension of the shaft 5. Bearing 9 is fitted with an external bearing housing 10 that is removable from the support 2, which "sits" on the trunnion of the internal axial center console of the housing cover 2 and is secured to it, for example, with pins and bolts. This allows you to ensure the minimum bore diameter of the heat exchanger body of the heat exchanger. The external bearing housing 10 has an axial hole in its end wall for the output of the shaft 5. The output of the shaft 5 from the hole in the external bearing housing is sealed in the same way as the seal 8. The labyrinth-breather seal is also not shown here conditionally, because it is not there is a subject of invention. On the side of the inner end of the shaft 5, there are made spaced parallel splines in which the splined end of the hinge shaft 12 is mounted, for example, on molybdenum disulfite grease. The second end of the hinge shaft 12 is connected by its flange, for example, to the first wheel of the turbine 13. Since the possible mutual angular displacements of the compressor and turbine shafts are undoubtedly relatively small, the hinges of the shaft 12 can be all kinds of, including with cardan hinges, but instead of needle bearings, it is preferable to use anti-friction bushings and even with high-temperature grease. The articulated shaft 12 is pre-balanced in place with the turbine and with the compressor shaft until everything else is installed in the engine by rotation with a shaft-turning device or a starter. At the inner end of the outer bearing housing 10, on the landing centering belts and on the flanges, a support device 14 of the front support 15 of the inner housing 16 of the turbine and the combustion chamber is fixed. The connection of the front support 15 with the support device 14 is preferably slotted for the convenience of vertical assembly and disassembly of the compressor unit with the turbine unit in the housing 1 with the turbine at the top. / On the contrary / the shaft of the turbine 17 is installed in the housing cover 3. The angular contact bearing 18 of the shaft of the turbine 17 is mounted on the shaft against the groove in the shaft of the turbine and in the external bore in the housing cover 3 and is likewise fixed by the cover 19 with the shaft outlet turbines. The sealing of the turbine shaft is carried out similarly to the compressor shaft bearing 4. Angular contact bearing 18 can also be made in the form of a block of bearings, including in the form of a block of radial and thrust bearings or in the form of 2 ^x angular contact bearings. The cover 19 of the bearing 18 is mounted on the cover-housing 3 similarly to the cover 8. On the outer end of the turbine shaft against the bearing 18, for example, a spline sleeve 20 is installed, which extends from the cover 19 to the outside. The sleeve 20 is made in a block with a conical oil-saving disc. Emphasis on the outer end of the sleeve 20, emerging from the cover 19, on the splined end of the shaft of the turbine 17 is installed splined flange of the turbine shaft, not shown conditionally. This spline flange is fixed to the turbine shaft with a nut, not shown conditionally. On the inner part of the turbine shaft 17 and at the stop in the hub of the turbine wheel and similarly to Figs. 7-25 from L-14 on page 253, a thermally insulating and cooled sleeve 21 is preferably installed, and a support roller bearing 22 is mounted on its groove in the stop against it. Both the sleeve 21 and the inner ring of the bearing 22 are fixed by a common ring 23 mounted “hot” in a shallow, several microns, groove on the turbine shaft. The groove under the ring is preferably made by grinding with smooth radius transitions. The seal of the sleeve 21 on the shaft of the turbine 17 is conventionally not shown. Outside, the bearing 22 is equipped with an external bearing housing 24 with a groove-bed in it for the bearing 22 with the same purpose to ensure the minimum mounting diameter of the support bearing of the heat exchanger of the heat exchanger. And the outer bearing housing 24 is “seated” on a trunnion of the minimum diameter of the inner cantilever part of the housing cover 3 and is fixed on it with pins and bolts. The supporting element 25 of the turbine housing 16 is axially symmetrically fixed to the flange of the outer bearing housing 24 on the centering groove, and at the same time it also acts as a bearing cover 22. For this, it has a central hole for the turbine shaft to exit through it, and also having a seal cavity with an oil protection sleeve around shaft outlet. A centrifugal oil-saving disc 11 ^{and the} seal is seated on the groove of the thermally insulating sleeve 21. The labyrinth-prompter seal is conventionally not shown and is performed similarly to the well-known. For this is not the subject of invention. The supporting element 25 of the inner housing of the turbine 16 has an aerodynamically profiled flow part for trouble-free movement of exhaust gases through it into the recuperator. Its spacer elements are connected to the inner casing of the turbine 16, preferably with pins and bolts. Also, a welding option is also possible. The wheel disk of the second turbine 17, referring to the direction of movement of the working fluid, can be made integral with the turbine shaft, as well as separately, as, for example, in FIG. 5.03 in L-9 on page 114, or as in FIG. 2.14 in L-14 on page 54. And this is also not the subject of invention. The turbine wheel disks are interconnected by a power spacer 26, such as, for example, in FIG. 5.01 in L-9 on p. 112, on pins and bolts. The guide vanes of the turbine 27 and 28 are attached, for example, to the inner casing of the turbine 16, for example, using pins 29 and 30 passing, for example, through hollow vanes, including with the possible use of springs with plates, or elastic washers with information about them below, or with bolts and nuts for the shelves of the blades, as, for example, in Fig. 5.23 on p. 129 and as in Fig. 5.22 on p. 134 in L-9. Seals of the flow part of a gas turbine engine, including turbines, are conventionally not shown, because they are also not the subject of the invention. They are well known and can be performed, for example, similarly to FIG. 5.04 in L-9 on page 115. The turbine, including its nozzle and rotor blades of the wheels, is preferably made effectively cooled. However, their cooling system is not conventionally shown, because it is also not the subject of this invention. Cooling systems are very diverse and well known, although they are not without drawbacks.

In a gas turbine engine, an annular combustion chamber 31 is preferably used, similar, for example, to FIGS. 9.23–9.25 in L-9 on pages 386–387. The combustion chamber is also not an advantage of the invention and therefore is not considered in detail. The combustion chamber is preferably mounted on the inner housing of the turbine 16 and preferably in the same manner as in conventional gas turbine engines, including with the possible use of studs, springs, plates and nuts, pos. 32. And its output part is preferably telescopically connected to the turbine nozzle assembly of ^stage 1 or from the plenum in other types of combustion chamber. Aerodynamically profiled support elements of the front support 15 of the inner turbine housing 16 extend towards the inner turbine housing, preferably in between the heat pipes.

The compressed gas of the gas turbine engine from the compressor 6 is preferably discharged through an annular air duct 33, mounted, for example, on the lid-casing 2 from its outer side. For the axial passage of compressed working air through the cover-casing 2, a corresponding annular passage is preferably made in it. In this regard, the peripheral part of the lid-housing 2 is preferably connected to its central part by aerodynamically profiled support-force elements. Between the housing cover 2 and preferably the annular combustion chamber 31, preferably installed is a heated compressed engine working air after the compressor, preferably an annular heat exchange body 34 of the exhaust gas heat recuperator and preferably coaxial to the axis of the turbine and compressor, and intensively rotating on a bearing 35 mounted, for example, on a neck the inner center-center console of the housing cover 2. The bearing 35 is preferably self-centering. On both sides of the bearing 35, sealing rings 36 are preferably mounted with outer sealing surfaces made in radius. A bearing housing 37 is mounted on the outer ring of the bearing 35. The bearing housing 37 preferably has cooling oil channels included in the lubrication and cooling system, not conventionally shown. On both sides of the bearing 35 is closed by oil sealing caps 38, mounted on the bearing housing 37, for example, bolts. The seal between the covers 38 and the rings 36 is, for example, centrifugal-labyrinth-prompter. The inner shell 39 of the heat exchange body 34 is supported on the bearing housing 37 through thermally compensating support elements 40. An expanding annular transition 41 is mounted between the housing cover 2 and the heat exchange body 34, mounted, for example, on the housing cover 2. The heat exchange body is conventionally sealed at both ends thereof not shown and performed, for example, by a labyrinth, similar to the sealing of the flow part of the turbine and compressor. The peripheral shell 42 of the heat exchange body 34 is connected to the peripheral shell 43 of the heat exchange body 44 of the exhaust gas heat exchanger installed after the turbine and which removes heat from the exhaust gas, the connecting element 45, made, for example, in the form of a pipe and rotating together with the heat exchange bodies 34 and 44 between the outer casing of the turbine 1 and the inner casing of the turbine 16. The connecting element 45 is preferably connected limited axially telescopically movably with the shells of the heat exchange bodies 34 and 44. This is done in the case of a significant difference in temperature of the outer casing of the turbine 1 and the inner casing of the turbine 16 after starting and heating the turbine engine. In this case, the centering and transmission of torque between the heat exchange bodies and the connecting element is proposed to be performed, for example, on wide slots of the trapezoidal profile or on several dowels, preferably evenly spaced around the circumference, for example, as recommended in Fig.2.43a and 2.43b in L- 14, on page 70. The heat exchange body 44, installed after the turbine and preferably pine with it, is preferably mounted on a self-centering bearing 46 mounted, for example, on the neck of the inner axial center console of the housing cover 3, similar to the bearing 35. And also has similar sealing rings 47 on both sides. the outer ring of the bearing 46 is similarly mounted oil-cooled bearing housing 48 with side sealing caps 49. The bearing housing 48 is similarly connected to the inner shell 50 of the heat transfer t ate 44 thermal compensating support element 51. Both thermal compensating supporting elements 40 and 51 are preferably made directed from the bearing housings up and towards each other, and their root parts are preferably and respectively directed towards the axis of the turbine and compressor and towards the housing covers 2 and 3. To exit the exhaust gases from the heat exchange body 44, a similar annular passage is made in the lid-casing 3, and the peripheral part of the lid-casing 3 is connected to its central part by aerodynamically profiled op weight distribution, load-bearing elements. The seal of the heat exchange body 44 is also not shown conditionally and is performed similarly to the heat exchange body 34. The sealing of the oil system, including the lubrication system of the bearing 46 and cooling of its housing, is performed similarly to the bearing 35.

In a very "saturated" figure 1, for simplicity of the image, a simplified embodiment of the heat-compensating support elements 40 and 51 of the heat-exchange bodies 34 and 44 is presented, and similarly, for example, to the shown version in Fig. 3.21 and Fig. 3.22 in L-9 on page 70 and 71. However, it is undoubtedly preferable to connect the inner shells 39 of the heat exchange body 34 and 50 of the heat exchange body 44 to the bearing housings 37 and 48 using the articulated arms 52, as shown in FIG. 2 and FIG. 3, which is a combined section along A -A figure 2. The bearing housings 37 and 48 preferably have an annular or helical oil-cooling cavity 53. The bearing housings 37 and 48 are pivotally connected to the levers 52 by means of brackets 54 on the housings and pins 55, which are secured against falling out by snap spring rings 56. And with shells 39 and 50 of the heat exchange bodies levers 52 are connected by brackets 57 and fingers 58, fixed by locking rings 56. The outer shells 42 and 43 of the heat exchange bodies are connected to the connecting element 45 on the wide slots 59 of the trapezoidal profile in the "stop" in the heated work than the state at the ends of the spline grooves of the connecting element. Adjustment of the stop of the slots in the end of the grooves is carried out, for example, by moving in the axial directions of the bearings of the heat exchange bodies on their support journals by a set of adjusting rings or by thrust adjusting screws-crackers on the connecting element and the presence of spring buffers in the ends of the slotted grooves, excluding the axial "walking" of the connecting element on the outer shells of heat exchange bodies. The use of high temperature grease in splined joints is preferred. The support arms 52 on each of the supports of the heat exchange bodies are preferably evenly distributed around the circumferences of the inner shells and their number should be at least 3 ^x -4 ^x .

The complex support node on the lid-housing 2 can be performed, for example, and as in figure 4. In this case, the outer bearing 4 of the shaft 5 of the compressor 6 is installed on the shaft and in the housing similarly to figure 1 in the bore of the external tide of the cover-housing 2 and on the shaft 5 by the ring 7. The internal bearing 9 of the shaft 5 is installed in the bore of the inner cantilever support of the cover-case 2 and it is closed by a cover 60 installed in the bore of the housing-cover under the bearing 9, which is secured around the periphery, for example, by bolts in the end face of the housing-cover 2. However, their connection can also be made on flags, for example, bolts with nuts. And the support bearing 35 of the heat-exchange body 34 may already be mounted on the outer support neck of the cover 60. The bearing housing 37 and the support element 40 of the heat-exchange body are carried out similarly to the already noted. Sealing and lubrication of bearings are conventionally not shown and are performed in a known manner. The splined end of the articulated shaft 12 is mounted likewise in the internal splines of the shaft 5. The front support 15 of the inner housing of the turbine 16 is preferably mounted on the splined trunnion of the cover 60.

Another embodiment of the integrated support on the lid-housing 2 is shown in Fig.5. The front angular contact bearing 4 of the shaft 5 of the compressor 6 is mounted on the shaft similarly to the sleeve 7 and is installed in the front bore of the housing cover 2 and is closed by the cover 8 with a seal. The front angular contact bearing can also be complex and contain an additional thrust bearing or 2 angular contact bearings. The inner thrust bearing 9 is preferably made with cylindrical rollers, providing trouble-free thermal expansion of the shaft 5 along the outer ring of the bearing 9. The bearing 9 is preferably "inserted" in the groove of the shaft 5 "hot" with heating in oil. The outer ring of the bearing is fixed by an additional sleeve 61. The seal of the output of the shaft 5 is similar and preferably complex. A bearing 35 of the heat-exchange body 34 is mounted on the neck of the console cover of the housing-body 2. The bearing is axially fixed by the support 62, which is “hot” in the micro-groove of the pin of the inner console of the housing-cover 2. The spline peripheral end of the support 62 is a support of the front support 15 of the turbine’s inner case 16. The external cooled housing 37 is similarly mounted on the bearing 35. The bearing 35 is sealed, for example, with a complex centrifugal-labyrinth seal 63. The splined end of the articulated shaft 12 is installed in the internal splines of the shaft 5. The articulated the end of the shaft 12 may also be the shaft of the turbine 3-reference gas turbine engine.

The 3-support gas turbine engine with the shafts of the turbine and compressor can also be made with an intermediate intermediate support, which is fixed, including on the inner casing of the turbine 16. And this can also be done with a complex support, fastened, for example, with pins to the casing 16 through hollow nozzle blades of a turbine of the ^1st stage, for example, as in Fig. 5.23 in L-9 on page 129, but with reference to Fig. 1 according to the invention, or as in Fig. 2.6 in L-14 on page 50.

Intensive rotation of the heat exchange bodies 34 and 44 together with the connecting element 45 is preferably performed forced, including to ensure forced pumping of the working fluid through the heat exchange bodies. This provides a sufficiently close to zero hydraulic losses by the working fluid of the engine. One of the possible options for the rotation mechanism of heat transfer bodies is shown in Fig.6. The shaft 5 of the compressor 6 together with the driving gear 64 fitted onto it, for example, 2 ^x dowels 65, with distance sleeve 66 between the pinion 64 and the bearing 4 secured to the shaft 5 of the sleeve 7 'planted on hot "inserted in osetsentralnuyu bore in the housing cover 2, where the bearing 9 with the spacer sleeve 61 is already pre-installed and secured by the housing 8 mounted on the housing cover 2, for example, with bolts. The cover 8 is pre-mounted on the shaft 5 to the bearing 4. The hinge shaft 12 is also inserted into the internal splines of the shaft 5. The inner end of the shaft 5 is also sealed with a complex seal 11 made on the shaft 5 and on the support 67 of the front support 15 of the inner turbine housing 16. Support 67 is centered, for example, along the inner ring of the bearing 35 of the heat exchange body 34 and is fixed to the housing cover 2, for example, by bolts. The front neck of the shaft 5 is sealed in the axial bore of the gear cover 68 with a complex seal, containing, for example, an oil shielding sleeve with a shoulder 69 and a centrifugal ejector 70. The cover 8 is attached to the cover 2, for example, via the cover spacer 71 with screws or bolts 72. And the gear cover 68 itself is fastened, for example, at its periphery, for example, by bolts to the housing cover 2. On the housing cover 2, the housing 73 is made. In the housing 73, bearings 74 of the intermediate shaft 75 are mounted. On the shaft 75 it is mounted, for example, on a key gear a gear wheel 76 engaged with the gear 64, and a drive gear 77 is mounted at the other end of the shaft 75, for example, on a key. The gear wheel 76 and the drive gear 77 are spaced apart from the bearings 74, for example, by the intermediate sleeves 78 and secured by the snap rings 79. Outer the housing 37 of the bearing 35 at its periphery has a ring gear turned in radius. The gear ring of the bearing housing 37 engages with the drive gear 77. The support elements 40 of the heat exchange body 34 are centered, for example, on the outer ring of the bearing 35 and are secured, for example, by bolts 80. The inner part of the drive is closed by a cover 81 attached to the housing cover 2, for example, with bolts. A comprehensive seal between the cover 81 and supporting elements 40 of the heat exchange body 34 is performed in a similar manner, including a centrifugal ejector 82 mounted on the gear housing 37 of the bearing 35, and an oil shield with a shoulder around the axial hole in the cover is made on the cover 81. The labyrinth-prompter seal is conventionally not shown completely, but only partially. The seal of the bearing 35 is also performed by a complex centrifugal prompter-labyrinth containing, for example, internal o-rings 83 on the support element 40 and external o-rings 84 on the support 67. At the root of the support element 40 there are radial-axial channels 85 for draining oil collected centrifugal forces between rings 83.

One embodiment of a heat exchange body, in particular heat exchange body 44, is shown in FIGS. 7, 8 and 9. It has, for example, an inner shell 50 with inner brackets 57 for connecting to the support arms 52 and an outer shell 43 connected to the connecting element 45, for example, on flanges 86 and 87. In this case, the connecting element is made integral, for example telescopic, and its components can be made interconnected on wide centering slots, as noted above, including, for example, on fig.2.43a and 2.43b in the L-14 on page 70. The shells 43 and 50 of the heat exchange body 44 are made, for example, with a slight conical expansion in the direction of movement of the working fluid. Between the outer and inner shells, heat exchange elements are installed and fixed, made, for example, in the form of coils 88 coiled from pipes, of different diameters and mounted coaxially to each other and balanced relative to the axis of rotation of the heat exchange body and with relatively small air gaps between the turns in the coil layers and with air gaps between the layers of tubular coils for movement of the working fluid in them, including in radial directions. The coil tubes both in the layers and between the layers are fastened together by interlayer combs 89, and between the coils 88 and the shells 50 and 43 of the support combs 90 and 91, on which they are pre-assembled on pins 92 and inserted into the assembly between the shells and secured between the shells , for example, with bolts 93 and, if necessary, with spring washers 94 / see B-B /, performed, for example, according to the type of FIG. 236 in the book of P. I. Orlov. Design Basics. Moscow. Engineering. 1977 Volume 1 / L-15 /, p. 364 and, for example, from a high-temperature spring alloy ХН80ТБЮА. See, for example, Guidelines. Properties of steels and alloys used in boiler turbine construction. Part 3. CCTI. Leningrad. 1967 / L-16 /, p. 29. The support combs 90 and 91 are fixed in shells and end pins 95. The internal cavities of the coil tubes 88 are preferably filled with an intermediate liquid metal coolant, for example sodium or lithium. See, for example, B. G. Ganchev et al. Nuclear power plants. Moscow. Energoatomizdat. 1990 / L-17 /, pp. 70-71. The output tubes 96 from the coils are removed, for example, from the heat exchange body through radial holes made in the joint of the flanges 86 and 87 / axis along the joint plane / in accordance with the balancing conditions uniformly spaced around the circumference. See view B in Fig. 8. The inlet tubes are preferably inserted in the same way through the same radial holes made along the plane of the flange joints, and evenly around the circumference in accordance with the balancing conditions and rotated by a “duck” or simply by 90 ° and laid between the layers of coils, between combs and in the axial direction are laid to the other end of the coils. Combs 89, 90 and 91 are preferably aerodynamically profiled in accordance with the angular velocity of rotation of the heat exchange body, the radii of rotation of the combs and the relative speed of the working fluid washing the combs, as well as providing a fan effect on the working fluid, providing forcing the working fluid through the flow part, at least , heat exchange body to exclude hydraulic losses in the working fluid, which greatly affect the internal efficiency of a gas turbine engine. See L-5 on pages 74-89. The outlet edges of the combs are preferably pointed. The heat exchange body 34 is similar. The outlet tubes from the coils of the heat exchange body installed after the turbine / 44 / are connected to the inlet tubes of the coils of the heat exchange body 34 installed after the compressor, circulation tubes 97, laid, for example, through the connecting element 45, and the outlet tubes from the coils of the heat exchange body 34, installed after the compressor, similarly connected to the inlet tubes of the coils of the heat exchange body 44 installed after the turbine, by the circulation tubes 98 in accordance with the hydraulic circuit shown and 10, where poz.100 - working medium gas turbine engine to the heat exchanger, and poz.101 - working fluid after the heat exchanger. And in accordance with the diagram of FIG. 10, the circulation system preferably comprises an expansion pipe of the intermediate coolant and its supply 102 and a receiver for the coolant in the vapor phase 103 having a device 104 for replenishing the coolant in the circulation system. Due to the fact that during intensive rotation of the heat exchanger, the intermediate coolant will be in the field of centrifugal forces and its cooler part will be in the peripheral part of the circulation circuit, and the hotter part of the coolant will be closer to the rotation axis, therefore, expansion tubes 102 and receivers of the circulation circuits made directed towards the axis of rotation, but preferably not radially, but in the form of a part of the circumferential tube 102 of FIGS. 7 and 9, smoothly lowering below the tubes of the corresponding coil by a minimum ΔR, of a sufficient volume expansion. The expansion tubes 102 are fixed in the beds of the combs offset from the axis of rotation and are preferably made of tubes of a larger diameter than the tubes of the coils. Preferably, the circulation tubes 97 and 98 are also made with a large diameter. And, as can be seen in view D of FIG. 7, shown in FIG. 9, tees 103 are connected to the coil tubes, and the circulation tubes 96 and expansion tubes 102 are already connected to them. Tee 103 can be pre-docked with conical transitions to circulation and expansion tubes. At the end of the expansion tubes 102, the end tees 104 are docked with a muffled axial end and with the tubes 105 connected to the coolant expanders in the vapor phase, performed, for example, in the form of bellows and installed, for example, in the inner cavity of the inner shell 50. This detail is conditionally not shown.

где S_R - минимальная толщина стенки без прибавка, Р - давление в трубке, Д_a - диаметр трубки, [δ] - допускаемое напряжение, φ - коэффициент прочности. Для бесшовных труб φ=1. Смотрите, например, Нормы расчета на прочность стационарных котлов и трубопроводов пара и горячей воды. РД 10 - 249 - 98 Москва. Росгостехнадзор. 2003 /Л-18/, стр.47. В связи с чем трубки змеевиков предпочтительно выполняются минимального диаметра по условиям т/обмена и циркуляции теплоносителя в них. Это обеспечивает максимальное снижение толщины теплопроводной стенки между рабочим телом и промежуточным теплоносителем и одновременно увеличивает объемную площадь теплопередачи между ними.It is known that the minimum wall thickness of the tube of heating surfaces and pipelines is directly proportional to the diameter of the tube and the internal pressure of the medium in it. See, for example, the expression

where S _R is the minimum wall thickness without increase, P is the pressure in the tube, D _a is the diameter of the tube, [δ] is the allowable stress, φ is the strength coefficient. For seamless pipes, φ = 1. See, for example, Standards for calculating the strength of stationary boilers and pipelines of steam and hot water. RD 10 - 249 - 98 Moscow. Rosgostekhnadzor. 2003 / L-18 /, p. 47. In connection with this, the tubes of the coils are preferably made of a minimum diameter according to the conditions of t / exchange and circulation of the coolant in them. This ensures the maximum reduction in the thickness of the heat-conducting wall between the working fluid and the intermediate coolant and at the same time increases the volumetric heat transfer area between them.

The preference for the design of heat-exchange elements in the form of twisted tubular coils is that the voltage in the walls of the tubes, even intensively rotated in the form of rings, does not depend on the thickness of their walls, which allows for maximum thermal conductivity of the walls of the tubes, since the voltage in the rotating ring is determined by the expression δ = ρu ^2/201 / see, e.g., G.S.Zhiritsky and V.A.Strunkin. Design and strength analysis of parts of steam and gas turbines. Moscow. Engineering. 1968 / L-19 /, p. 187, where u is the peripheral speed, ρ is the density.

. Смотрите, например, Л-19, стр.41, где u₂=ωR₂, u₁=ωR₁ и где R₂-R₁=ΔR и при ΔR=0 внутреннее давление Р=0. С этой целью смотрите фиг.7, диаметры начала змеевика Д_макс и диаметры конца змеевика Д_мин предпочтительно выполняются минимальными, вплоть до Д_макс-Д_мин=0. Минимальной выполняется и величина ΔR - радиальная длина трубки расширения. Смотрите фиг.7.A decrease in the heat-conducting wall thickness of the coil tubes is achieved by lowering the working pressure in the coil tubes. For the internal pressure in the rotating channel relative to some axis of rotation with an angular velocity ω and located from the axis of rotation at distances from R ₁ to R ₂ is determined by the expression

. See, for example, L-19, p. 41, where u ₂ = ωR ₂ , u ₁ = ωR ₁ and where R ₂ -R ₁ = ΔR and when ΔR = 0 the internal pressure is P = 0. For this purpose, see Fig. 7, the diameters of the beginning of the coil D _max and the diameters of the ends of the coil D _{min are} preferably minimal, up to D _max -D _min = 0. The minimum value is fulfilled and the value ΔR is the radial length of the expansion tube. See FIG. 7.

For the same purpose, the diameters of the coils from the D _min side installed after the turbine are preferably the same with the diameters of the D _min coils installed after the compressor. The diameters of the D _max coils installed both after the turbine and after the compressor are also preferably the same.

For the same purpose, preferably coils are connected in pairs with the same D _min and D _max , but installed on opposite sides of the turbine.

For the same purpose, the outlet 96 and inlet radial tubes of the coils and the connecting circulation pipes 97 and 98 between the coils of the heat exchange bodies installed on both sides of the turbine are preferably located at diameters greater than D _max , or at least not less than D _min .

For the same purpose, it is preferable to individually install circulation pumps 99 in the circulation circuits of each pair of coils and with a minimum working pressure, or even two in each circuit before entering the coils with half pressure, or it is possible to install a multi-section pump. Large diameters of the circulation pipelines and, accordingly, their large wall thicknesses will not naturally affect the heat transfer.

The heat-exchange elements of heat-exchange bodies can be made 2- and 3- or more inlets, meaning with the same D _max and D _min , but with an increased winding pitch and with coils embedded in each other and installed closer to the outer shell, at, for example, a one-way coil near the inner shell of the heat-exchange body, or external coils must have significantly higher mass flow rates of the coolant, including both increased diameters of the tubes and the speeds of the coolant. Heat exchange elements can be made in the form of multilayer installed sets of pipes, wound along a helical line, including with extended winding steps, in which the pipe even forms part of the coil, and other options for the execution of heat exchange bodies are possible.

The internal cavity of the gas turbine engine is preferably thermally insulated and cooled. The external casing of the gas turbine engine is also preferably thermally insulated to eliminate heat loss to the environment.

The issue of circulation pumps is not the subject of the present invention. However, firstly, there are already sufficiently operable sodium circulation pumps used, for example, at the BN-350 reactor of a nuclear power plant. See, for example, Fig. 7.70 in L-17 on page 402.

There are also known electromagnetic induction pumps for pumping liquid metal coolants. See, for example, patent No. 1144588 A1 / L-20 /. There is also its own constructive solution of an electric induction pump, but this is already the subject of another invention.

The recuperator rotor has an automatic dynamic balancing system, not conventionally shown in the attached drawings.

The rotor of the exhaust gas heat recovery apparatus preferably comprises an automatic dynamic balancing system, although not conventionally shown in the accompanying drawings, but is undoubtedly understandable as well.

Why, for instance, each of the heat exchange bodies 34 and 44 resting on the bearing housing 48 4 ^mja support arms 52 are installed, e.g., 2 actuators, such as "stepping" type, is screwed or unscrews rezbosoderzhaschie balancing-loads body threaded radial openings formed in the heat exchange bodies and arranged in two mutually perpendicular ^x and diametrically axial planes passing through the axis of the fingers 55 of levers 52. to monitor increased c / b recuperator force on the rotor in any Lieb or in any of the radial directions, and preferably in the central cavities of the cooled CCD on the levers 52 are attached, for example, wire strain gauges. Silicon or germanium compression strain gauges with operating temperatures from -60 ° C to + 200 ° C can also be installed in the cooled bearing housings 48. Wire - from -100 ° C to + 400 ° C. Strain gauges are connected in pairs in the shoulders of the electric bridge circuits of control devices for actuators. The electrical circuits have disconnecting devices of a variable current component in the electrical circuits of the load cells from the circulating effect of the weight of the rotor on them. A more detailed description of the execution of actuators and their control devices will be presented in additional applications for inventions, because they cannot be included in the scope of this application.

The rotor drive of the exhaust gas heat recuperator can be either hydraulic or electric, including a rotating electromagnetic field.

GTE work

Смотрите, например, Х.Хаузен. Теплопередача при противотоке, прямотоке и перекрестном токе. Москва. Энергоиздат. 1981 г. /Л-23/, стр.23 и 36, гдеThe proposed gas turbine engine works similarly to the already known regenerative gas turbine engine. However, there are significant differences, namely, after heating the gas turbine engine, the compressed working air from the compressor passes directly through the heat exchange body, which heats it, where it, washing the heat transfer tubes of the coils, heats up and then enters the combustion chamber. In this case, the working air passing through the heat exchange body does not have pressure losses, since it is forcedly pumped by aerodynamically profiled combs, like the blades of axial machines. Already heated working air in the combustion chamber will burn the injected fuel inside itself without any problems, heating up to operating temperature. After the combustion chamber, the working fluid expands in the turbine, as usual, and does the work, including compressing the working air in the compressor, pumping the working fluid through the heat exchanger bodies of the recuperator to drive the fuel and oil pumps. However, a substantial part of the turbine's work remains for useful work. After the turbine, the exhaust gases flow straight into the heat exchange body, where the heat transfer tubes of the coils will take heat to a temperature close to the temperature of the compressed working air after the compressor. And similarly, the exhaust gases will pass through the heat exchange body without hydraulic losses due to the forced pumping of the exhaust gases by combs shaped as blades of axial machines. The heat exchange bodies installed both before and after the turbine and interconnected by a telescopic sliding sliding connecting element rotate on bearings by a drive mechanism. Considering that there is no compression of the working fluid in the heat-exchange bodies, and the comb-blades are aerodynamically profiled and have sharp output edges, and the coil tubes of the coils are close to each other, the drive will not be large, but the thermodynamic cycle will be close enough to the theoretical and also because regeneration will be close to ideal. In this case, the heat-exchange bodies will have a significantly smaller heat-exchange surface, which means that they will have smaller dimensions and weight due to the more efficient heat transfer method implemented in the gas turbine engine according to RF patent No. 2130156. The transfer of the heat flux taken from the exhaust gases by the heat exchange elements in the heat exchange body 44 to the heated working air by the heat exchange elements in the heat exchange body 34 is preferably carried out by a liquid metal coolant, preferably forcibly circulating between the heat exchange elements of the heat exchange bodies installed both before and after the turbine. The efficiency of the transfer of large heat fluxes by liquid metal coolants is confirmed by their satisfactory operation in nuclear power plants, including the transfer of these heat fluxes to much greater distances than between GTE heat exchangers installed both before and after the turbine. The effectiveness and essence of the heat transfer method according to the patent of the Russian Federation No. 2130156 is described in the description of the patent. However, in short, the essence is that during normal heat transfer between the medium and the heat exchange surface of a heat exchange body and for any degree of turbulence, the turbulent pulsations of the medium decay intensively as they approach the wall, and the velocity of the medium on the wall itself is 0. This is a phenomenon " sticking. " It takes place as a result of the phenomenon of adsorption between the medium and the surface of the body. However, these forces are relatively small. See, for example, B.V. Nekrasov. Fundamentals of General Chemistry. TI. Moscow. Chemistry. 1973 / L-21 /, pp. 266-268. As a result, in the near-wall layer of the medium there is a thermal sublayer, within which the transfer of heat between the flow of the medium washing the heat-exchange body and the heat-exchange surface of the body is carried out by molecular heat conductivity. See, for example, V.A. Grigoriev and V. M. Zorin. Heat and mass transfer: a thermotechnical experiment. Moscow. Power Publishing. 1982 / L-22 /, pp. 162-163. And in accordance with L-22, the thermal conductivity of air is more than 8490 times worse than that of a well heat-conducting copper metal. See, for example, table 2.3 in L-22 on pages 119-120, where the thermal conductivity of copper, at 573 K, is 371 W / m K, and in table 2.20, on page 159, the thermal conductivity of air, at 300 ° C, is 4.37 10 ^-2 W / mK. In general, it is well known that stationary air is a very good thermal insulator. In the proposed gas turbine engine, the tubes of the coils intensively rotate relative to the axes of the compressor and the turbine, and the elements of the working fluid / molecule, etc. / fly up to the surfaces of the rotating tubes of the coils, collide with them and heat exchange with them. The same molecules of the working fluid, which in this case “adhere” to the surfaces of the walls, at the same instant will find themselves in intensive rotational motion along with the surfaces on which they “sit”. As a result, they instantly find themselves in a field of centrifugal forces. And it is the intensity of rotation of the heat exchange bodies that must be such that the centrifugal forces on the elements of the working fluid exceed the adsorption forces. As a result, the elements of the working fluid after collision with the heat-exchange surface and after the resulting heat exchange with it will be instantly discarded from the "backs" and sides of the coil tubes and discarded from the belly of the tube, for example, like a top. As a result, intense turbulent pulsations of the working fluid, already coming from the heat-exchange surfaces, will occur, which is not the case with the usual method of heat transfer. As a result, direct kinetic heat transfer between the medium and heat exchange surfaces without molecular heat conduction and at the wall surfaces will be carried out. And the heat transfer intensity will undoubtedly be determined by the thermal conductivity of the walls of the tubes, the thickness of which, as noted above, can be minimized. Since it is possible to provide a highly efficient heat transfer between the inner surface of the walls of the tubes of the coils and the liquid metal coolant. Since, firstly, the liquid metal coolant in the internal channels will also be in the field of centrifugal forces, there is no problem to ensure a higher coolant temperature at the backs of the heat transfer tubes and lower at the abdomen of the coil tubes in both heat transfer bodies, including those in heated , as well as in cooling, including the worst cooling of the coolant in the back zone, including an increase in the thermal resistance of the back walls of their slightly larger thickness with respect to the rest of the walls of the tubes. This will provide a slightly higher density of the coolant at the backs. And the lifting force in the field of centrifugal forces will provide for the forced circulation of the coolant in the near-wall zones of the tubes. See, for example, L-19 on pages 40-41. Secondly, good turbulence without centrifugal forces can also be provided in the tubes of the coils for the coolant transported in the tubes with a relatively small thickness of the thermal sublayer according to the expression for the Reynolds number

See, for example, H. Hausen. Heat transfer in countercurrent, forward flow and cross current. Moscow. Power Publishing. 1981 / L-23 /, p. 23 and 36, where

v is the coolant velocity, d is the tube diameter, υ is the kinematic viscosity.

And according to Table 2.21 in / L-22 / on page 159, the kinematic viscosity coefficient, for example, liquid metal sodium, for example, at 500 ° C is 27.2 · 10 ^-8 m ² / s, while for water, for example, at 50 ° C, the kinematic viscosity coefficient is only 0.56 · 10 ^-6 m ² / s. See, for example, P.G. Kiselev. Handbook of hydraulic calculations. Moscow. Energy. 1974 / L-24 /, p. 13. Thirdly, the thermal conductivity, for example, of liquid metal sodium in the thermal sublayer near the walls of the tubes, for example, at 500 ° C, is 63.8 W / μ. See, for example, Table 2.21 in L-22 on page 159, while, for example, the thermal conductivity of water, for example, at 90 ° C is only 68 · 10 ^-2 W / μ, i.e. almost 100 times worse. See, for example, table 2.18 in L-22 on page 157, and the thermal conductivity of dry air at 500 ° C is only 5.45 · 10 ^-2 , i.e. more than 1000 times worse than liquid metal sodium. See table 2.20 in L-22 on page 159.

Fourthly, in horizontal tubes there is also free convection. See, for example, L-24 on pages 38-39.

And undoubtedly, the above guarantees the creation of highly efficient heat exchangers for exhaust gas heat up to the ideal degree of regeneration, and maintain the level of hydraulic losses in the air-gas path at a level close to 0.

And in accordance with the graphs in FIG. 56 to L-5 on page 70 and the graphs in FIG. 68 on page 81 with a hydraulic loss level close to zero and a degree of regeneration sufficiently close to 1 and even at T ₃ / T = 4.31, the internal efficiency of gas turbine engines created can be more than 50% even in gas turbine engines with theoretical adiabatic compression and expansion processes. The proposed gas turbine engine is also designed for the implementation of more advanced thermodynamic cycles, including the intensively cooled compression process up to isothermal and the heated expansion process up to isothermal, the internal gas turbine engine efficiency can exceed 60%. And when implementing the proposed gas turbine engine and the already reached level of maximum temperatures of thermodynamic cycles at the level of 1300-1400 ° С, see, for example, L-13, the table on page 66, then the gas turbine engines created will have an efficiency of 60-70%, depending on from implemented thermodynamic cycles and the degree of their proximity to theoretical ones.

Claims (18)

1. A gas turbine engine containing a compressor with a cooled compression process or with a theoretical adiabatic compression process, a device or device for igniting and burning fuel, a turbine cooled or uncooled, with a heated expansion process or with a theoretical adiabatic expansion process, a device or a device for heat recovery gases into the thermodynamic cycle of the engine, containing either a rotating heat-exchange body or rotating heat-exchange bodies heat-exchange elements, or with blocks of heat-exchange elements containing heat-exchange surfaces, washed by the working fluid of the engine, including working air after the compressor and exhaust gases after the turbine, characterized in that its heat-exchange device or exhaust heat recovery device is made or made in the form of a heat exchanger heat of the exhaust gases, and its heat exchange bodies are made spaced from each other and installed after the compressor, but before the turbine, and after the turbine, or They are not spaced apart before and after the turbine, but, for example, are made in the form of a heat exchange unit, and the heat exchange bodies of the exhaust gas heat recovery unit are made containing tubes, including not only round ones, either made containing elements of a tubular type, or from elements containing internal cavity-channels, and internal cavity-channels of heat-exchange elements of heat-exchange bodies are filled with an intermediate heat carrier and are included in the circulation system of the intermediate heat carrier between rotating heat exchangers heat exchanged elements heated by exhaust gases after the turbine, and rotating heat exchange elements heating the engine working air after the compressor, and heat exchange elements are balanced and coaxially or axisymmetrically installed in heat exchange bodies with countercurrent or with transverse countercurrent or countercurrent-angular washing of their heat exchanger elements the working fluid of the engine, and between them the tubular heat-exchange elements or heat-exchange elements of the tubular type are installed with annular gaps, whether more with inter-surface gaps for heat-exchange elements containing internal cavity channels for washing their external heat-exchange surfaces with a working fluid of the engine, including for the movement of the working fluid between them with radial components of its movement, the heat-exchange elements of the heat-exchanging bodies being rotated at an angular speed, providing a sufficiently intense separation from their external with respect to the axis of rotation of the heat exchange surfaces ("backs"), colliding with them and, accordingly, heat exchange the elements of the working fluid that are connected with them, and at the same time provide a sufficiently intense “discharge” of the working fluid elements from both the lateral heat-exchange surfaces and the “belly” of the heat-exchange surfaces that touch the heat-exchange surfaces and, accordingly, heat-exchange with them at the same time as they are sucked . 2. GTE according to claim 1, characterized in that the heat-exchanging bodies of its exhaust gas heat recovery unit are preferably installed along the one-way travel of the working fluid of the engine from the entrance to the GTE to the exit of the GTE, including after the compressor and after the turbine, including including either the axis of rotation of the turbine and the axis of rotation of the compressor, including, for example, made rotating relative to the axis of rotation of the turbine and compressor, including those rotating at speeds other than the speed of rotation of the turbine and compressor, or heat exchangers bodies can also be made installed on a one-way travel of the working fluid from the entrance to its exit from the gas turbine engine and after the compressor, and after the turbine, and around the axis of rotation of the turbine and compressor, but are made, for example, rotating and not coaxial to the axis of rotation of the turbine and compressor, either made installed and not around the axis of rotation of the turbine and compressor and rotating around its own axis of rotation. 3. The gas turbine engine according to claim 1, characterized in that the heat exchange elements of the heat exchange bodies of the exhaust gas heat recovery apparatus are preferably balanced and coaxially or axisymmetrically mounted in its heat exchange bodies and are preferably made in the form of twisted tubular coils of different diameters, and are preferably installed one in the other, and another in the following, etc., including twisted tubular coils can be made and 2 coils of the same diameter with respectively longitudinally stretched turns and nested as if one in another with successive alternation of turns of one coil with turns of another coil, i.e. made as if in the form of 2 lead-in coils, and can also be made in the form of 3 or more lead-in coils, and can also be made in the form of spiral wound pipes with turns laid one next to the other in radial tube layers with side the gaps between the pipe coils, including stacked pipe coils and pipe coils, including radial clearances between the pipe layers, or heat exchange elements are made in the form of multilayer pipe sets, wound on a screw The lines, including those making up a part of the turn, are either made in the form of straight axis-longitudinal pipes, balanced and preferably axisymmetrically installed in heat-exchange bodies, or in the form of radially installed pipes, supported on the periphery of heat-exchange bodies, made, for example, of different lengths from the periphery heat exchange bodies as the circular cross-sectional area of the heat exchange body decreases as it approaches the axis of the heat exchange body, as well as, for example, in the form of non-straight radial pipes or in the form of radially branched pipes па snowflakes ’, either in the form of spirally wound tubular coils, or made up of tubular-type elements, and the heat-exchange elements are preferably made loose from one another, including in axial-longitudinal directions, including in radial layers, if any and also in the radial directions, including between the radial layers, if any, and also preferably mounted on the supporting elements of the heat exchange bodies by supporting-spacer elements, including aerodynamically profiled with their optimal flow around the working fluid, including those taking into account the angular speeds of rotation of the heat exchange elements of their radii of rotation and the speed of movement of the working fluid through the heat transfer bodies, including taking into account the accepted countercurrent or transverse countercurrent or countercurrent angular flow around the worker the body of the heat-exchange elements, and the input and output sections of the support-expansion and guide elements are preferably made with a difference of their input and output angles, providing forcible movement the working fluid through heat-exchange bodies. 4. The gas turbine engine according to claim 3, characterized in that the supporting-expansion and guiding elements of the heat-exchange bodies are made, for example, in the form of aerodynamically profiled combs, preferably made, at least, with mounting connectors along the axes of the beds in them under the heat-exchange tubes or under elements containing elements of a tubular type or of other profiles, including, if necessary, containing elastic support-spacer elements, including, if necessary, adjustable, including, preferably, “short-circuited” when heated m working condition of heat exchange bodies. 5. The gas-turbine engine according to claim 1, characterized in that the internal diametrical dimensions of the tubes of the heat-exchange elements, or the internal cavity-channels of the heat-exchange elements of a different type, or their equivalents, are preferably made with relatively small sizes, up to the minimum under conditions of a sufficiently effective circulation of intermediate coolant, including the terms of the efficiency of its heat exchange with the inner walls. 6. GTE according to claim 1, characterized in that the axis of the internal cavities-channels of the heat-exchange elements, including the axis of the tubes of the heat-exchange elements, then simply the internal cavities-channels of the heat-exchange elements, starting from the axes of the inlet openings to the heat-exchange elements to the outlet openings from heat exchange elements are preferably installed relative to the axes of their rotation with a relatively small radial-axial slope, bearing in mind that the heat carrier located in the heat exchange elements is in the field of centrifugal forces and varies with the temperature and, accordingly, its density in the direction of its movement in them, or the axis of the internal cavity-channels of the heat exchange elements are made without radial slope, and the axis of the outlet openings of the internal cavity-channels of the heat exchange elements installed after the compressor are preferably installed at the same radial distances from their rotation axes, as well as the axes of the circulation pipelines connected to them by either channels or channels, as well as the axes of the inlet openings of the channel cavities, the heat exchanger of the elements, refurbished after the turbine are preferably located at the same radial distances from their rotational axes as the axes connected to them by circulation pipelines, or channels, or channels, inlet openings of the cavity-channels of the heat exchange elements installed after the compressor, or at radial distances from their rotation axes, sufficiently close to the same, and the intermediate coolant circulation system preferably selectively connects the outlet openings from the cavity channels of the heat exchange elements entrances installed after the compressor, with the inlet openings of the cavity-channels of the heat exchange elements installed after the turbine and preferably located at the same radial distances from the axes of their rotation, or sufficiently close to the same, and preferably similarly interconnected by circulation pipes of the intermediate coolant outlet openings from the cavities -channels of heat-exchange elements installed after the turbine, with inlet openings of cavity-channels of heat-exchange elements, anovlennyh after the compressor. 7. GTE according to claim 6, characterized in that the intermediate coolant circulation system preferably contains circulation devices in each circulation loop, or contains an integral circulation device, either without it, or a non-selective intermediate coolant circulation system, and preferably each intermediate circulation loop the heat carrier between the heat exchange elements of the heat exchange bodies, or a single circulation circuit of the heat carrier between the heat exchange bodies preferably contains a cavity for the expansion cavities of the intermediate coolant, made, or made, for example, in the form of tubes or channels docked with them or channels with preferably a small deviation of the axes of their channel-cavities from the axial lines of the circles of the internal cavity-channels of the heat-exchange elements to the side to the axis of rotation, and the expansion cavity and the intermediate coolant supply, in turn, is preferably connected by pipelines or channels, or channels, or directly with individual or group combined-cycle expansion riviters, or with expanders of the vapor-gas medium, preferably made in the form of a bellows or bellows, or in the form of an expansion device, for example, containing a vapor-gas receiver of an excess volume of a vapor-gas medium, a compressor for pumping an excess volume of vapor-gas medium into a receiver from expansion cavities and an intermediate coolant reserve, including through a preferably contained intercooler, a check valve between the compressor and receiver, a pressure switch in the expansion cavity or in the cavity expansion and supply of a coolant for turning on and off a compressor, steam-gas reducers or reducer for returning a gas-vapor medium from a receiver into a cavity of expansion and stock of an intermediate coolant or into a cavity of expansion and stock of an intermediate coolant after a decrease in the volume of the medium or volumes of media as the coolant cools, for example, after TBG stops. 8. The gas turbine engine according to claim 1, characterized in that the tubes of the heat exchange elements of the heat exchange body or heat exchange bodies installed or installed after the compressor and preferably containing turbulent pulsations of the intermediate heat carrier in them are preferably made with a larger wall thickness of the backs than the abdomen . 9. The gas turbine engine according to claim 1, characterized in that the intermediate heat carrier circulation system between the heat exchange elements of its heat exchange bodies preferably contains its constituent elements, the flow parts of which pumping devices are preferably located at radial distances from the axis or from their rotation axes, not less than radial distances from the axis or from the axis of rotation of the internal cavity-channels of the heat-exchange elements connected by them. 10. A gas turbine engine according to claim 1, characterized in that the heat-exchanging bodies are preferably mounted through support-force elements on bearings, preferably mounted on the necks of the axial longitudinal bearings of the gas turbine engine, preferably made around the turbine and compressor shafts, or around the turbine and compressor shaft, and preferably coaxially with they, including those made, for example, on the transverse partitions of the casing of the gas turbine engine, and along the axes of these axial longitudinal supports, are preferably made longitudinal longitudinal cavities for passage of turbine shafts and comp essor, or the shaft of the turbine and compressor, as well as in the longitudinal support, preferably made internal radial-axial bore-bed for bearings of the shaft of the turbine and compressor, or the shaft of the turbine and compressor, or bore bed for the bearings of the shaft of the turbine and compressor, or shaft of the turbine and the compressor is made in the end caps-cases of the axial longitudinal supports, or the bed-bores for the bearings of the turbine and compressor shafts, or the turbine shaft and the compressor are made in the cup cases installed, for example, on the native bearings from the side of their inner ends after the bearings of the heat exchange bodies, counting from the transverse partitions of the GTE case, including, if necessary, the cup bodies are also made with large diameters of the bore-beds for the bearings of the turbine shaft and the compressor or the shaft of the turbine and compressor than the diameters bearing necks for bearings of heat exchangers on axial longitudinal bearings, and the transverse partitions of the casing of the gas turbine engine are preferably made containing central parts, including those containing axial longitudinal supports and peripheral parts attached to the body of the gas turbine engine, as well as containing annular passages between them, i.e. between the central and peripheral parts for moving the working fluid of the engine through them, and between themselves the central and peripheral parts of the transverse partitions of the casing of the gas turbine engine are preferably connected by aerodynamically profiled support-force elements, or the transverse partitions of the casing of the gas turbine engine are made without peripheral parts with the fastening of the support-force elements, for example, to the casing of the gas turbine engine, and the turbine engine of the gas turbine engine is preferably made comprising an inner casing with preferably fixed elements fixed to it the flow part of the turbine, and the inner turbine housing itself is preferably fixed through preferably aerodynamically profiled support-force elements to preferably the same axial longitudinal bearings as the bearings of the heat-exchange elements, including preferably after the bearings of the heat-exchange bodies, counting from the transverse partitions of the turbine engine body, or the turbine’s inner casing is fixed to the end caps of the longitudinal longitudinal supports, or to the existing end cover on some horizontal longitudinal supports, if any either the inner turbine housing is mounted on the housing-cups of the shaft bearings on the axial longitudinal bearings, or on the housing-glass of any of the longitudinal longitudinal supports, if they are either on the longitudinal longitudinal supports, or one of the supports of the internal turbine housing is mounted on the longitudinal longitudinal support after the bearing , then its other support can be installed on the end cap of the bearing either on the housing-cup, or one of the supports of the inner turbine housing is installed on the end cap of the bearing, then the other support can be mounted on housing, as well as any of the bearings of the shaft of the turbine and compressor, or any of the bearings of the shaft of the turbine and compressor are installed in the bore-beds of the housings or in the housing, made, for example, based on the inner housing of the turbine, or on supporting elements turbine housing 11. GTE according to claim 10, characterized in that the supporting force elements of its heat-exchanging bodies are preferably made based on bearings through rotating bearing housings and preferably contain limited heat-conducting elements, and are also preferably thermally compensated or containing thermal compensation devices. 12. GTE according to claim 11, characterized in that the heat-compensating devices of the support-strength elements of its heat exchange bodies are made, for example, containing at least three 2-link arms on each of the supports of the heat exchange bodies, and not lying in the same plane, or containing four 2-hinged levers or more, including preferably containing supporting and limiting elements of ultimate deformations, including preferably adjustable. 13. GTE according to claim 11, characterized in that the thermally compensated supporting-force elements of its heat-exchanging bodies are made, for example, containing elastically deformable elements, including preferably containing supporting-limiting elements of ultimate deformations, including preferably adjustable. 14. GTE according to claim 11, characterized in that the rotating support bearing housings of the support-force elements of its heat exchange bodies are preferably made cooled. 15. The gas turbine engine according to claim 1, characterized in that the heat-exchange bodies or blocks of the heat-exchange bodies of its exhaust gas heat recovery unit, installed both after the compressor and after the turbine and rotating preferably on bearings coaxially to the rotational axes of the turbine and compressor, are preferably interconnected, preferably balanced preferably coaxial or axisymmetric connecting element or elements, and in the area of the turbine, at least located or located around the periphery of the turbine, and preferably about containing or containing circulating channels for the intermediate coolant, or circulating tubes, or circulating tubes. 16. GTE according to claim 1, characterized in that it preferably contains a mechanism for forced rotation of the heat exchange bodies. 17. The gas turbine engine according to claim 1, comprising an exhaust gas heat recuperator, including a rotary recuperator rotor comprising a heat exchange body, a connecting element or connecting elements between them, supporting force elements of the heat exchange bodies, characterized in which preferably contains a device or device for automatic balancing of the rotor of the recuperator, including those containing or containing balancing bodies-weights mounted on the rotor of the recuperator, actuators, moving load balancing bodies, as well as tracking devices of increased centrifugal forces on the rotor of the recuperator in any or in any of the radial directions in comparison with the others, for example strain gauge devices installed, for example, on supporting-force elements of heat-exchanging bodies, and strain gauge devices are included, for example, in the electrical circuit of the control apparatus or in the electrical circuits of the control apparatus for actuators, including those containing or containing, for example p, elements of electric bridge circuits. 18. The gas-turbine engine according to claim 17, characterized in that the automatic balancing device of its recuperator rotor is made, for example, comprising rotary actuators rotating on the axes, for example, eccentrically located balancing load bodies, or is made, for example, containing rotary actuators and moving into radial or in radially containing directions (at an angle to the radius), for example, in thread-containing holes on the heat exchanger rotor, thread-containing balancing cargo bodies.

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