CN117266987A

CN117266987A - Jet split rotor supercharging gas turbine

Info

Publication number: CN117266987A
Application number: CN202210665461.5A
Authority: CN
Inventors: 韩培洲
Original assignee: Individual
Current assignee: Individual
Priority date: 2022-06-14
Filing date: 2022-06-14
Publication date: 2023-12-22
Also published as: WO2023241021A1

Abstract

A jet split-flow type rotor booster gas turbine comprises a gas compressor (21) and a turbine (23) connected through a shaft, wherein a rotor (25) with a plurality of rows of combustion chambers (26) is arranged between the gas compressor and the turbine, the rotor is arranged in a rotor shell (29), in the gas outlet arranged on the rotor shell, a part of working gas with highest temperature and pressure generated in the combustion chamber (26) is firstly generated by jetting or blowing through a corresponding gas pipe through a part of working gas, and then the rest of working gas in the combustion chamber is blown through the other part of gas outlet and the corresponding gas pipe to blow the turbine (23), so that the working gas generated in the combustion chamber is split through jetting, the working efficiency of the rotor booster gas turbine is improved, and the turbine blade is not required to be manufactured by special high-temperature resistant materials because the rest of working gas in the combustion chamber is correspondingly reduced, and the manufacturing cost of the gas turbine is also reduced.

Description

Jet split rotor supercharging gas turbine

The invention relates to a rotor supercharging gas turbine, in particular to a jet split-flow rotor supercharging gas turbine.

In the rotor pressurizing gas turbine with the application number of 202011068701.0, although the structure of a plurality of rows of combustion chamber rotors is optimized, fuel and air can form homogeneous fuel atomization mixed gas for combustion, but high-temperature and high-pressure working gas discharged from the rotor combustion chamber can be totally sprayed to the turbine for working, and the shaft power emitted by the gas turbine is high, in the rotor pressurizing gas turbine for an airplane, the direct post-spraying and jet diversion of the working gas generated by the rotor combustion chamber can possibly achieve better propelling effect.

The invention aims to provide a jet split-flow type rotor supercharged gas turbine, which not only ensures that the rotor supercharged gas turbine has high efficiency and high power, but also realizes the direct backward ejection and jet split-flow of the working gas function part generated by a rotor combustion chamber through structural improvement, thereby being beneficial to improving the propulsion working efficiency of the rotor supercharged gas turbine, and in addition, after the jet split-flow working of the high-temperature high-pressure working gas part in the rotor combustion chamber, the residual working gas temperature and pressure in the combustion chamber are correspondingly reduced, and the working running state of turbine blades in a turbine shell is improved.

The first gas pipe side-mounted rotor supercharging gas turbine comprises a jet split-flow rotor supercharging gas turbine, and comprises a gas compressor and a turbine connected through a machine shaft, wherein a rotor with a plurality of rows of combustion chambers is arranged between the gas compressor and the turbine, the rotor is arranged in a rotor shell, a plurality of equal gas distribution angle areas are divided on the rotor shell, a gas exchange inlet and a gas exchange outlet which are positioned in the same angle are sequentially arranged from the starting position in each gas distribution angle area to the tail end position in the rotating direction of the forward rotor on the rotor shell, an ignition cavity provided with a spark plug, a first gas outlet, a second gas outlet, a third gas outlet, a fourth gas outlet and a fifth gas outlet … … are sequentially formed after the gas exchange inlet and the gas exchange outlet, the air outlet end of the air compressor is communicated with the air exchanging inlet through a compressed air conveying pipe, the air exchanging outlet and the corresponding air outlets are respectively communicated with the corresponding air spraying openings on the nozzle plate in front of the turbine through corresponding air conveying pipes, after the first air outlet in each air exchanging angle area is communicated with the first air conveying pipe, the rear side of the first air conveying pipe extends backwards through the turbine shell from the periphery of the turbine shell, high-temperature high-pressure working fuel gas sprayed out of the first air outlet can be sprayed backwards from the first air conveying pipe, and the second air outlet, the third air outlet, the fourth air outlet and the fifth air outlet … … behind the first air outlet are respectively communicated with the corresponding air spraying openings on the nozzle plate in front of the turbine through corresponding air conveying pipes.

When only the first air pipe in the jet split-flow rotor booster gas turbine is used for performing jet work, each first air pipe communicated with the first air outlet in each air distribution angle zone extends backwards through the turbine shell, then extends into the tail nozzle at the rear part of the turbine shell, and the rear end of the first air pipe is communicated with the corresponding diffusion nozzle.

The rear side of the first air delivery pipe can be further arranged in such a way that after each first air delivery pipe communicated with the first air outlet in each air distribution angle area extends backwards through the turbine shell, the rear end of the first air delivery pipe is communicated with a diffusion nozzle attached to the periphery of the tail nozzle.

When the blades are also arranged at the rear side of the first air delivery pipe, each first air delivery pipe communicated with the first air outlet in each air distribution angle area extends backwards to the turbine shell, an air jet is formed at the rear end of the first air delivery pipe, the last-stage blades arranged at the rear side of the turbine are positioned at the outer side of the turbine shell, the tops of the last-stage blades are also connected with the connecting swivel, the connecting swivel is positioned at the outer side of the turbine shell, the diameter dimension of the front end face of the connecting swivel is the same as the diameter dimension of the rear end face of the turbine shell, double-acting outer ring blades are formed at the periphery of the connecting swivel, the air jet at the rear end of the first air delivery pipe is aligned with the outer ring blades at the periphery of the connecting swivel, a fan duct is further arranged at the periphery of the outer ring blades, the fan duct is connected with the turbine shell through a guide post piece, the outer ring blades adopt streamline cross section, the streamline center line is basically a straight line, the high-temperature high-pressure working gas turbine blades ejected from the air jet at the rear end of the connecting swivel have thicker arc front face and extend backwards, the air facing face and the back air face gradually become thinner, the double-acting outer ring blades are enabled to act as the air blades, the air flow is blown out from the outer ring duct to the outer ring duct, and then the air flow is blown out from the outer ring duct, and the outer ring duct acts as the air flow through the outer ring duct, and the fan.

When the double-acting outer ring blade is longer in size, the corresponding air jet ports at the rear side of each first air delivery pipe are also in a prolate shape and are obliquely arranged relative to the axis of the turbine, one side of each prolate air jet port is far away from the axis, the prolate air jet port at the other side is close to the axis, the width occupied by the long-sized air jet port enables the air jet port to correspond to a plurality of outer ring blades, the radial size of the narrow part of the oblate air jet port is smaller than the length of the outer ring blades in the radial direction, and the air flow which is blown by the outer ring blades passing through the air jet port can be blown to the root of the blades from the top of the blades.

In the jet split-flow rotor supercharged gas turbine of the third embodiment, the jet split-flow rotor supercharged gas turbine comprises a gas compressor and a turbine connected through a crankshaft, a rotor with a plurality of rows of combustion chambers is arranged between the gas compressor and the turbine, the rotor is arranged in a rotor shell, a plurality of equal gas distribution angle areas are divided on the rotor shell, a gas exchange inlet and a gas exchange outlet which are positioned in the same angle are sequentially arranged from the initial position in each gas distribution angle area on the rotor shell to the tail end position in the rotating direction of the rotor, an ignition cavity provided with a spark plug, a first gas outlet, a second gas outlet, a third gas outlet, a fourth gas outlet and a fifth gas outlet … … are sequentially formed after the gas exchange inlet and the gas exchange outlet, the gas outlet end of the gas compressor is communicated with the gas exchange inlet through a compressed air pipe, the gas exchange outlet and the corresponding gas outlets are respectively communicated with corresponding gas outlets on a nozzle plate in front of the turbine through corresponding gas pipes, the last stage blades are arranged at the outer side of the turbine shell, the blade tops of the last stage blades are also connected with a peripheral connecting swivel, the connecting swivel is arranged at the rear of the turbine shell, the diameter size of the front end face of the connecting swivel is the same as that of the rear end face of the turbine, peripheral outer ring blades are also formed on the connecting swivel, a flaring turbine shell which covers the outer ring blades therein is arranged at the periphery of the outer ring blades, the flaring turbine shell is connected with the rear side of the turbine shell through a baffle ring, a first air outlet in each air distribution angle area and two air outlets at the middle and final positions respectively extend backwards along the periphery of the turbine shell through respective air delivery pipes, air nozzles are formed at the rear ends of the air delivery pipes, and the air nozzles at the rear ends of the air delivery pipes are aligned with the outer ring blades after passing through the baffle ring between the flaring turbine shell and the turbine shell, the size of the air jet opening at the rear end of each air delivery pipe is wider, so that each air jet opening can be fully arranged in an annular air jet opening arrangement space between the flared turbine shell and the turbine shell, and besides a first air outlet in each air distribution angle area and two air outlets at the middle and final positions, the rest air outlets are respectively communicated with each corresponding air jet opening on a nozzle plate in front of the turbine through corresponding air delivery pipes.

In order to reduce the working temperature of the blades, cold air delivery pipes with intercoolers are respectively led out from each compressed air delivery pipe behind the air compressor, the number of the cold air delivery pipes is the same as that of the distribution angle areas on the rotor shell, cold air jet ports are also formed at the rear ends of the cold air delivery pipes, and after the cold air delivery pipes are uniformly distributed among other delivery pipes and pass through baffle rings connected with the flaring turbine shell and the turbine shell, the cold air jet ports at the rear ends of the cold air delivery pipes are aligned with the outer ring blades behind.

In order to enable the power of the turbine to be output, the last-stage blades at the rear side of the turbine and the outer ring blades connected into a whole can be arranged on the rotor body of the turbine and also can be arranged on a separate rotor disc on the power output shaft.

In the jet split-flow rotor supercharged gas turbine of the fourth embodiment, the jet split-flow rotor supercharged gas turbine comprises a gas compressor and a turbine connected through a crankshaft, a rotor with a plurality of rows of combustion chambers is arranged between the gas compressor and the turbine, the rotor is arranged in a rotor shell, a plurality of equal gas distribution angle areas are divided on the rotor shell, a gas exchange inlet and a gas exchange outlet which are positioned in the same angle are sequentially arranged from the initial position in each gas distribution angle area to the tail end position in the rotating direction of the rotor, an ignition cavity with a spark plug, a first gas outlet, a second gas outlet, a third gas outlet, a fourth gas outlet and a fifth gas outlet … … are sequentially formed after the gas exchange inlet and the gas exchange outlet, the gas exchange outlet and the corresponding gas outlet are respectively communicated with the corresponding gas outlet on a nozzle plate in front of the turbine through corresponding gas pipes, the last stage blades arranged on the rear side of the turbine are positioned on the outer side of the turbine shell, the blade tops of the last stage blades are connected with a connecting swivel, the connecting swivel is positioned behind the turbine shell, the diameter size of the front end face of the connecting swivel is the same as that of the rear end face of the turbine shell, peripheral outer ring blades are formed on the connecting swivel, peripheral connecting outer rings are also formed on the blade tops of the outer ring blades, fan blades are also formed on the connecting outer ring, a nozzle shell is arranged on the periphery of the rear side of the turbine shell, the rear side of the turbine shell is connected with the rear side of the nozzle shell arranged on the periphery through a baffle ring, the diameter size of the rear end face of the nozzle shell is the same as that of the rear end face of the connecting outer ring provided with blades, a fan duct for covering the fan blades therein is also arranged on the periphery of the fan blades, the fan duct is connected with the nozzle shell at the periphery of the turbine shell through a guide column sheet, a first air outlet and two air outlets at the middle and final positions in each air distribution angle area are respectively extended backwards along the periphery of the turbine shell through respective air delivery pipes, air outlets formed at the rear ends of the air delivery pipes penetrate through baffle rings between the nozzle shell and the turbine shell and are aligned with outer ring blades at the rear, the air outlets at the rear ends of the air delivery pipes are wider in size, so that the annular air outlets between the nozzle shell and the turbine shell can be fully exhausted through the air outlets, the first air outlet and the two air outlets at the middle and final positions in each air distribution angle area are respectively communicated with corresponding air outlets on a nozzle disc in front of the turbine through corresponding air delivery pipes, and a structure body consisting of final stage blades, outer ring blades and fan blades at the rear of the turbine is arranged between a rotor body of the turbine and a tail cone at the rear side of the turbine through bearings.

In order to cool the blades, the air-conditioning air pipes with intercoolers are led out from the compressed air pipes behind the compressor, the number of the air-conditioning air pipes is the same as that of the air distribution angle areas on the rotor shell, the rear ends of the air-conditioning air pipes are also provided with air-conditioning air nozzles, and after the air-conditioning air pipes are uniformly distributed among other air-conditioning air pipes and pass through baffle rings connected with the nozzle shell and the turbine shell, the air-conditioning air nozzles at the rear ends of the air-conditioning air pipes are aligned with the outer ring blades at the rear.

In the improved jet split-flow type rotor supercharging gas turbine, the first gas pipe is arranged in a side-arranged mode to extend backwards, so that a high-temperature high-pressure power gas part generated in the rotor combustion chamber can be directly ejected backwards, and the propulsion efficiency is correspondingly improved, and the jet split-flow type rotor supercharging gas turbine is particularly suitable for being used as a power device of a high-speed aircraft and a large and medium-sized unmanned aerial vehicle. The partial working gas is split, and the split of the high-temperature high-pressure working gas is used for blowing the outer ring blades which can be cooled, so that the rest working gas with correspondingly reduced temperature and pressure can drive the turbine to operate and drive the compressor, and the turbine blades do not need to be made of special high-temperature resistant materials under the condition of improving the working efficiency, so that the manufacturing cost of the turbine blades is reduced.

Description of the drawings the jet splitter rotor supercharged gas turbine according to the invention is described in detail below with reference to the accompanying drawings.

FIG. 1 is a cross-sectional view of a jet splitter rotor booster gas turbine of the present invention.

FIG. 2 is a cross-sectional view of a rotor casing and a rotor of the jet splitter rotor boost gas turbine taken along line A-A of FIG. 1.

FIG. 3 is a cross-sectional view of a jet splitter rotor supercharging gas turbine tail nozzle taken along line B-B of FIG. 1.

FIG. 4 is a cross-sectional view of a jet splitter rotor booster gas turbine according to a second embodiment of the invention.

FIG. 5 is a cross-sectional view of the aft structure of the jet splitter rotor booster gas turbine taken along line A-A of FIG. 4.

FIG. 6 is a cross-sectional view of the double acting vane taken along line B-B in FIG. 4.

FIG. 7 is a sectional view of a configuration of a jet splitter rotor booster gas turbine according to a third embodiment of the invention.

FIG. 8 is a cross-sectional view of a jet splitter rotor booster gas turbine according to a fourth embodiment of the invention.

FIG. 9 is a cross-sectional view of the aft structure of the jet splitter rotor booster gas turbine taken along line A-A of FIG. 8.

Detailed description of the inventionthe jet splitter rotor booster gas turbine of the present invention is generally configured as shown in fig. 1 and 2 and includes a compressor 21 and a turbine 23 connected by a crankshaft 22. Between the compressor and the turbine there is a rotor 25 with several rows of combustion chambers 26, which rotor is housed in a rotor housing 29. The rotor case 29 is divided into a plurality of equal distribution angle areas 40, and as shown in fig. 2, the rotor case 29 is divided into three equal distribution angle areas 40 (in the case of a high-power rotor booster gas turbine, four distribution angle areas may be provided), each distribution angle area occupies an angle area of 120 degrees. From a starting position in each distribution angle zone 40 on the rotor housing 29 to an end position of rotation of the forward rotor 25 in the direction of arrow 56, a ventilation inlet 8 and a ventilation outlet 7 are provided in sequence, which are at the same angle. After the ventilation inlet 8 and the ventilation outlet 7, an ignition cavity 31 provided with a spark plug 30, a first air outlet 1, a second air outlet 2, a third air outlet 3, a fourth air outlet 4 and a fifth air outlet 5 and … … can be formed in sequence, and the corresponding working gas outlets after the ventilation outlet 7 are respectively communicated with corresponding gas nozzles on a nozzle disc 37 in front of a turbine through corresponding gas delivery pipes.

In the connection of the air outlet end of the air compressor with the ventilation inlet 8, as shown in fig. 1, the air outlet end of the air compressor 21 is communicated with the ventilation inlet 8 through a compressed air delivery pipe 9, and the ventilation outlet 7 is communicated with an air jet 7' on a jet disc 37 through a delivery pipe 17. In fig. 1, the state that the combustion chamber 26 is communicated with the ventilation inlet and the ventilation outlet when the combustion chamber is rotated to the positions of the ventilation inlet 8 and the ventilation outlet 7 is shown by the angular deflection, at this time, compressed air flowing out from the compressor 21 is filled into the combustion chamber 26 through the compressed air delivery pipe 9 and the ventilation inlet 8, medium-pressure working gas in the combustion chamber is extruded, the medium-pressure ventilation process in the combustion chamber is completed, and the medium-pressure working gas discharged from the ventilation outlet 7 is sprayed to the turbine 23 at the rear side through the corresponding gas delivery pipe 17 and the gas spraying port 7'. In practice, the compressed air delivery pipe 9 is further provided with a fuel nozzle (not shown) for forming a fuel mixture. In the three air distribution angle areas 40 on the rotor shell 29 in the embodiment of fig. 2, after the air exchanging inlet 8 and the air exchanging outlet 7, an ignition cavity 31 provided with a spark plug 30, a first air outlet 1, a second air outlet 2, a third air outlet 3, a fourth air outlet 4, a fifth air outlet 5 and a sixth air outlet 6 are sequentially arranged, and after the first air outlet 1 in each air distribution angle area 40 is communicated with a first air delivery pipe 11, the rear side of the first air delivery pipe extends backwards from the periphery of the turbine shell 24 to the turbine shell and then extends into a tail nozzle 19 at the rear part of the turbine shell, and the rear end of the first air delivery pipe 11 is communicated with a corresponding diffusion nozzle 20, so that high-temperature high-pressure working gas sprayed out from the first air outlet 1 can be sprayed backwards through the first air delivery pipe 11 and the diffusion nozzle 20, and part of working gas discharged from the first air outlet 1 can directly generate jet acting force. The second air outlet 2, the third air outlet 3, the fourth air outlet 4, the fifth air outlet 5 and the sixth air outlet 6 after the first air outlet 1 are respectively communicated with the corresponding air nozzles on the nozzle plate 37 through the corresponding air pipes 12, 13, 14, 15 and 16, so that the working gas with correspondingly reduced temperature and pressure can be sequentially depressurized and sprayed outwards from the second air outlet 2 and the following air outlets, and then sprayed to the turbine 23 from the corresponding air nozzles on the nozzle plate 37 through the corresponding air pipes to drive the turbine to rotate for working, and the turbine 23 also drives the air compressor 21 to continuously generate compressed air while rotating for working.

In practice, the flow cross section of the first air outlet 1 is increased or decreased, so that the amount of the working fuel gas entering the first air delivery pipe 11 can be increased or decreased, and the size ratio between the direct injection driving force of the high-pressure fuel gas and the turbine jet driving force can be determined. Under the condition of ensuring that the turbine 23 can drive the compressor 21, more working gas is sprayed from the first air outlet 1 as much as possible so as to increase the driving force generated by direct injection of the high-pressure working gas.

In practice, it is also possible to let the first gas delivery pipes 11 in the respective gas distribution angle regions 40, which communicate with the first gas outlet 1, not extend into the tail pipe 19 after extending rearward through the turbine housing 24, but rather to let the rear ends of the first gas delivery pipes communicate with the diffuser nozzles 20 attached to the periphery of the tail pipe 19 (not shown).

In order to reduce heat loss generated when working gas flows through the first gas pipe 11, at least the first gas pipe 11 should be provided with a heat insulating layer 41. In addition, in practice, a corresponding forced oil nozzle may be disposed in the diffuser 17 at the rear end of the first air delivery pipe 11, so as to flexibly increase the air injection force.

When the jet split-flow type rotor booster gas turbine is used as the power of an airplane, part of working gas in a combustion chamber can be directly ejected backwards and larger reverse ejection pushing force is generated, so that the working efficiency of the rotor booster gas turbine is improved, the rest working gas with correspondingly reduced temperature and pressure is used for pushing the turbine to operate, the working temperature of turbine blades is also reduced, the operating condition of the turbine blades is improved, and the turbine blades do not need to be manufactured by using materials with special high temperature resistance.

In the second embodiment of the present invention shown in fig. 4, in order to convert the power gas emitted backward from the first gas delivery pipe 11 into a larger forward driving force, a double-acting outer ring blade is provided behind the gas ejection port at the rear side of the first gas delivery pipe 11. In this embodiment, as shown in fig. 4, in each of the gas distribution angle regions 40 (see fig. 2) of the rotor case 29, after each of the first gas delivery pipes 11 communicating with the first gas outlet 1 in each of the gas distribution angle regions 40 extends rearward to the turbine case 24, gas nozzles 38 are formed at the rear ends of the first gas delivery pipes 11. The last stage blades 42 provided on the rear side of the turbine 23 are positioned outside the turbine shell 24, and the tips of the last stage blades 42 are also connected to the connecting swivel 39 so that the connecting swivel is positioned outside the turbine shell 24. The diameter of the front end face of the connecting swivel is the same as that of the rear end face of the turbine shell 24, which corresponds to the continuation of the rear end of the turbine shell 24 to the rear tail nozzle, double-acting outer ring blades 36 are further formed on the periphery of the connecting swivel 39, and air nozzles 38 at the rear end of the first air delivery pipe 11 are aligned with the outer ring blades 36 on the periphery of the connecting swivel 39. After the combustion chamber 26 on the rotor 25 is communicated with the first air outlet 1 on the rotor shell 29, the working fuel gas with highest temperature and pressure in the combustion chamber is sprayed out from the first air outlet to the outside, and the outer ring blade 36 is blown through the air spraying port 38 at the rear end of the first air conveying pipe, so that the double-acting outer ring blade can generate larger forward pushing force as a fan when rotating, and a fan duct 43 is arranged at the periphery of the outer ring blade and connected with the turbine shell 24 through a guide post piece 45.

The double acting outer ring blades 36 behind the air jets 38 are of streamlined cross section (see fig. 6), the streamlined center line 51 being substantially straight, the outer ring blades provided at the periphery of the connecting swivel 39 having a thicker arcuate front face 52 and rearwardly extending, progressively thinner windward and leeward faces 53, 54. Of course, in order to allow uniform backward exhaust of the outer ring blades at different radii, the windward angle of the outer ring blades will be correspondingly twisted from the blade root to the blade tip. The action of the double-acting outer ring blades 36 with the working gas and the air flow is shown in fig. 6, and the high-temperature high-pressure working gas ejected from the air nozzle 38 at the rear end of the first air delivery pipe blows the outer ring blades 36 along an arrow 58, so that the outer ring blades are subjected to the rotation acting force shown by the arrow 57, and the double-acting outer ring blades 36 play the role of a turbine. After the outer ring blades rotate past the air jets 38, the outer ring blades in turn pressurize and discharge the incoming air flow from the front side of the fan duct 43 in the direction indicated by arrow 59, allowing the double acting outer ring blades 36 to act as a fan again, thereby increasing the forward thrust of the gas turbine. Of course, the cross-sectional shape of double-acting blades 32 is neither a good turbine blade shape nor a good fan blade shape, but is only a compromise between acting gas blow-down work and exhausting back as a fan.

In practice, when the double-acting outer ring blades 36 are made to be longer, as shown in fig. 5, the air nozzles 38 at the rear side of the corresponding first air delivery pipes 11 are also in a prolate shape, and are obliquely arranged relative to the axis of the turbine, so that one side of the prolate air nozzle is far away from the axis, the prolate air nozzle at the other side is close to the axis, and the width of the elongated air nozzle 38 occupies the width so that the air nozzle can correspond to the plurality of outer ring blades 36, and the air flow ejected by the air nozzle 38 can be blown onto the plurality of double-acting outer ring blades 36 at the same time. The radial dimension of the flat narrow part of the air jet 38 is smaller than the length of the outer ring blade 36 in the radial direction, so that the air flow jetted by the air jet 38 can only blow on part of the area of the double-acting blade, and the air jet 38 which is obliquely arranged also enables the outer ring blade which rotates through the air jet to blow to the root of the blade from the top of the blade, so that the blown double-acting blade cannot bear too large power gas impact force. Since three gas distribution angle zones 40 (see fig. 2) are provided on the rotor housing 29, after the gas nozzles 38 on the rear side of the first gas delivery pipe 11 of each gas distribution angle zone extend toward the rear double acting outer ring blade 36, as shown in fig. 5, there are three gas nozzles 38 at 120-angle intervals aligned with the double acting outer ring blade.

If the size of the double-acting outer ring blade 36 is relatively short, the radial size of the air jet 38 at the rear side of each first air delivery pipe 11 is substantially the same as the radial length of the double-acting outer ring blade 36 (not shown).

In the second embodiment rotor booster gas turbine shown in fig. 4, although the working gas stream having the highest temperature is discharged from the gas nozzles 38, the double-acting outer ring blades 36 are cooled by the high temperature gas stream which is then reacted with the cool air which has previously entered, so that the working temperature of the double-acting outer ring blades is not very high, and no additional cooling of the blades is necessary.

A third embodiment of a jet splitter rotor booster gas turbine is shown in fig. 7, and the gas turbine's compressor 21, rotor housing 29 and rotor 25 are substantially identical to those of the first and second embodiments, and include a compressor 21 and a turbine 23 connected by a shaft, between which is disposed a rotor 25 with several rows of combustion chambers 26, the rotor being housed in the rotor housing 29, and a plurality of equal distribution angle areas 40 (see fig. 2) being defined on the rotor housing 29, and a ventilation inlet 8 and a ventilation outlet 7 being provided in the same angle in sequence from a start position in each distribution angle area 40 on the rotor housing 29 to an end position in the direction of rotation of the rotor 25, and after the ventilation inlet and the ventilation outlet, an ignition chamber 31 with a spark plug 30, a first air outlet 1, a second air outlet 2, a third air outlet 3, a fourth air outlet 4 and a fifth air outlet 5 … … being formed in sequence, the ventilation outlet 7 and the corresponding air outlets thereafter being respectively communicated with corresponding ports on a nozzle plate 37 in front of the turbine via corresponding air delivery pipes.

The third embodiment differs from the first embodiment in that, in addition to the first gas delivery pipes 11 which are separately arranged, further corresponding gas delivery pipes are separately arranged on the rotor case 29, and that these separately arranged gas delivery pipes are allowed to blow further outer ring blades with gas nozzles on the rear side thereof. The separate air delivery pipes and the outer ring blades are shown in fig. 7, and the final stage blades 42 arranged at the rear side of the turbine 23 are positioned at the outer side of the turbine shell 24, and the tips of the final stage blades 42 are also connected with a peripheral connecting rotary ring 39, and the connecting rotary ring is positioned at the rear of the turbine shell 24, and the diameter size of the front end face of the connecting rotary ring is the same as the diameter size of the rear end face of the turbine shell 24, which is equivalent to the extension of the rear end of the turbine shell 24 to the rear tail nozzle. Also formed on the connecting swivel 39 is an outer peripheral ring blade 32, the outer periphery of which is provided with a flared turbine shell 27 which houses the outer ring blade therein, the flared turbine shell being connected to the rear side of the turbine shell 24 via a baffle ring 28.

After the outer ring blade 32 is formed on the final stage blade 42 through the connecting swivel 39, the first air outlet 1 and the two air outlets in the middle and final positions in each air distribution angle area 40 respectively extend backwards along the periphery of the turbine shell 24 through respective air delivery pipes, air nozzles 38 are formed at the rear ends of the air delivery pipes, and after the air nozzles at the rear ends of the air delivery pipes pass through the baffle ring 28 between the flared turbine shell 27 and the turbine shell 24, the rear outer ring blade 32 is aligned. If the third embodiment in fig. 7 adopts the same rotor case structure as the first and second embodiments, three air distribution angle areas 40 (see fig. 2) are divided on the rotor case, and first to sixth air outlets are provided in each air distribution angle area 40 of the rotor case 29, after the first air outlet 1 passes through the baffle ring 28 between the flared turbine case and the turbine case via the first air delivery pipe 11 with the air outlets 38 at the rear end of the air delivery pipe and is aligned with the outer ring blade 32 at the rear, the air delivery pipes of the two air outlets arranged at the middle and final positions are also arranged to be separated outwardly, i.e., the air delivery pipes 14 and 16 of the fourth air outlet 4 (or the third air outlet 3) and the sixth air outlet 6 are also arranged to be separated outwardly, and the corresponding air outlets 38 at the rear sides of the two air delivery pipes are aligned with the outer ring blade 32 at the rear through the baffle ring 28. The gas nozzles 38 at the rear end of each gas delivery pipe are formed in a wide size so that each gas nozzle can be discharged to fill the annular gas nozzle arrangement space between the flared turbine housing 27 and the turbine housing 24.

In the corresponding gas duct arrangement of the gas outlets on the rotor housing 29, the remaining gas outlets in the respective gas distribution angle regions 40 on the rotor housing 29 are in communication with the corresponding gas jets on the nozzle plate 37 in front of the turbine 23 via the corresponding respective gas ducts, respectively, except for the first gas outlet 1 and the two gas outlets in the middle and final position in the respective gas distribution angle region 40.

In the third embodiment of fig. 7, since the respective air delivery pipes of the first air outlet, the fourth air outlet and the sixth air outlet are separately arranged (the arrangement of the air outlets is shown in fig. 2), the remaining second air outlet 2, third air outlet 3 and fifth air outlet in each air delivery angle area 40 of the rotor case 29 are communicated with the respective air nozzles on the nozzle plate 37 in front of the turbine 23 via the respective air delivery pipes. In fig. 7, the deflection angle depicts the process of communicating the ventilation inlet with the ventilation outlet when the combustion chamber 26 on the rotor is rotated to the position of the ventilation inlet 8 and the ventilation outlet 7, and allowing medium pressure ventilation in the combustion chamber, the ventilation outlet 7 is opened to the corresponding air jet on the jet disc 37 via the air delivery pipe 17.

In a typical gas turbine, the higher the temperature before the turbine, the higher the efficiency of the gas turbine, but the higher the temperature required for the turbine blade to withstand the working gas increases the manufacturing cost of the turbine blade. In the jet splitter rotor booster gas turbine of the third embodiment of fig. 7, since the working gas at the highest temperature has been ejected from the first gas outlet, the working gas temperature flowing out from the remaining gas outlets has been relatively reduced, and accordingly, the operating temperature of the turbine blades has been reduced, improving the turbine operating conditions.

Since Gao Wenzuo power gas sprayed from the first gas outlet also can bear high gas temperature of the blown blade, in order to avoid overheating of the outer ring blade, as shown in fig. 7, cold gas pipes 48 with intercoolers 49 can be led out from each compressed air gas pipe 9 behind the compressor 21, meanwhile, the number of the cold gas pipes is the same as that of the gas distribution angle areas 40 on the rotor shell, cold gas spraying ports 50 are formed at the rear ends of the cold gas pipes, after the cold gas pipes 48 are uniformly distributed among other gas pipes and pass through the baffle ring 28 connecting the flared turbine shell 27 and the turbine shell 24, the cold gas spraying ports at the rear ends of the cold gas pipes are aligned with the rear outer ring blade 32, the cooled compressed air blows and cools the outer ring blade 32, so that the temperature of the outer ring blade does not particularly rise, and the turbine blade does not need to be manufactured by special high temperature resistant materials.

In practice, the last stage blades 42 and the integrally connected outer ring blades 32 on the rear side of the turbine 23 may be mounted on the rotor body 33 of the turbine 23, or as shown in fig. 7, the last stage blades 42 and the integrally connected outer ring blades 32 on the rear side of the turbine 23 may be mounted on a separate rotor disk 34 on the power output shaft 35, so that the rotor-supercharging gas turbine outputs power to the outside through the power output shaft 35. Of course, in order to enable the outer ring blade 32 to generate more power, the connecting swivel 39 may be extended backward, and a first stage outer ring blade (not shown) may be further disposed behind the outer ring blade 32. Since the jet splitter rotor booster gas turbine in the embodiment of fig. 7 outputs power primarily by the power take-off shaft 35, it can be used as a power plant for a propeller aircraft, helicopter, vehicle, ship, and power station.

A fourth embodiment of a jet splitter rotor booster gas turbine, shown in fig. 8, is substantially identical in construction to the first, second and third embodiments, and also includes a compressor 21 and a turbine 23 connected by a crankshaft 22. Between the compressor and the turbine there is a rotor 25 with several rows of combustion chambers 26, which rotor is housed in a rotor housing 29. A plurality of equal air distribution angle areas 40 (see fig. 2) are divided on the rotor shell 29, a ventilation inlet 8 and a ventilation outlet 7 which are positioned in the same angle are sequentially arranged from the initial position in each air distribution angle area 40 on the rotor shell 29 to the tail end position in the rotating direction of the forward rotor 25, an ignition cavity 31 provided with a spark plug 30, a first air outlet 1, a second air outlet 2, a third air outlet 3, a fourth air outlet 4 and a fifth air outlet 5 … … are sequentially formed after the ventilation inlet and the ventilation outlet, and the ventilation outlet 7 and the corresponding air outlets are respectively communicated with corresponding air jet openings on a nozzle disc 37 in front of a turbine through corresponding air delivery pipes. In the fourth embodiment of fig. 8, the structure of the rotor case 29 may also be the same as that of the first embodiment (see fig. 2), three air distribution angle regions 40 (four air distribution angle regions may be provided for a high-power model) are provided on the rotor case, and a first air outlet 1, a second air outlet 2, a third air outlet 3, a fourth air outlet 4, a fifth air outlet 5, and a sixth air outlet 6 are provided in each air distribution angle region, and six air outlets are provided.

The jet splitter rotor booster gas turbine of the fourth embodiment is mainly used as a power plant of a jet aircraft, as shown in fig. 8, last stage blades 42 provided at the rear side of a turbine 23 are positioned at the outer side of a turbine casing 24, the tips of the last stage blades 42 are connected with a connecting swivel 39, the connecting swivel is positioned at the rear of the turbine casing 24, and the diameter dimension of the front end face of the connecting swivel is the same as the diameter dimension of the rear end face of the turbine casing 24, which corresponds to the continuation of the rear end of the turbine casing 24 to the rear tail nozzle. The connecting rotor 39 is further formed with outer ring blades 32, the outer ring 41 is further formed on the tip of the outer ring blades 32, and the fan blades 44 are further formed on the connecting outer ring.

The rear side of the turbine shell 24 is provided with a nozzle shell 46, the rear side of the turbine shell 24 is connected with the rear side of the nozzle shell 46 arranged on the periphery through a baffle ring 28, the diameter size of the rear end surface of the nozzle shell 46 is the same as the diameter size of the front end surface of the rear connecting outer ring 41 provided with blades, and the rear end of the nozzle shell 46 is extended to the rear through the connecting outer ring 41. A fan duct 43 is provided around the periphery of the fan blades 44 to house the fan blades therein, and the fan duct is connected to a nozzle casing 46 around the periphery of the turbine casing 24 through guide post blades 45, so that the jet split-flow type rotor supercharged gas turbine with this structure becomes a jet engine with a rear-mounted fan duct.

In the arrangement of the air delivery pipes for each air outlet on the rotor housing 29, the first air outlet 1 and the two air outlets in the middle and final positions in each air distribution angle region 40 extend backward along the periphery of the turbine housing 24 through the respective air delivery pipes, and the air nozzles 38 formed at the rear ends of the air delivery pipes are aligned with the rear outer ring blades 32 through the baffle ring 28 between the nozzle housing 46 and the turbine housing 24.

The gas nozzles at the aft end of each gas delivery tube are relatively wide in size, as shown in FIG. 9, so that each gas nozzle 38 can be displaced to fill the annular gas nozzle placement space between the nozzle housing 46 and the turbine housing 24. Except for the first air outlet 1 and the two air outlets in the middle and final positions in each air distribution angle area 40, the rest air outlets are respectively communicated with corresponding air nozzles on the nozzle plate 37 in front of the turbine 23 through corresponding air delivery pipes.

In the connection arrangement of the air outlets (see fig. 2) on the rotor housing 29 with the air ducts, the first air outlet 1, which is arranged separately, opens via the air duct 11 into the baffle ring 28 between the nozzle housing and the turbine housing, and the air jet 38 at the rear end of the air duct is aligned with the outer ring blade 32 behind. After the first air outlet, as shown in fig. 9, the corresponding air delivery pipes 14 and 16 of the fourth air outlet and the sixth air outlet in the middle and the last position can be led to the baffle ring 28, so that the working fuel gas with higher temperature and pressure can push the outer ring blade 32 and drive the fan blade 44 at the periphery of the outer ring blade, and the working fuel gas can generate larger forward pushing force through the fan blade. The corresponding gas pipes 12, 13 and 15 of the remaining second, third and fifth gas outlets 2, 3 and 5 in each gas distribution angle area 40 on the rotor shell are communicated with the corresponding gas nozzles on the nozzle plate 37 in front of the turbine 23, so that the working gas with correspondingly reduced temperature drives the turbine 23 in the turbine shell 24 to rotate for working, and the operation condition of the turbine is improved.

Since the rotational speed of the fan blades is relatively reduced, the structure of the final stage blades 42, the outer ring blades 32 and the fan blades 44 behind the turbine 23 is bearing-mounted between the rotor body 33 of the turbine and the rear end cone 47.

As the temperature of the fuel gas sprayed out of the first air outlet Gao Wenzuo is very high, in order to avoid overheating of the outer ring blades, as shown in fig. 8, the cool air delivery pipes 48 provided with the intercooler 49 are respectively led out from each of the compressed air delivery pipes 9 behind the air compressor 21, the intercooler 49 is arranged in the cooler shell 60, the cool air enters from the air inlet 61 on the cooler shell, takes away the compression heat of the compressed air flowing through the intercooler 49, and then flows out from the air outlet 62 on the cooler shell. The number of the cold air delivery pipes 48 connected with the intermediate cooler 49 is the same as that of the distribution angle areas 40 on the rotor shell, and cold air jet ports 50 are formed at the rear ends of the cold air delivery pipes, and after the cold air delivery pipes 48 are uniformly distributed among other air delivery pipes and pass through the baffle ring 28 connecting the nozzle shell 46 and the turbine shell 24, the cold air jet ports 50 at the rear ends of the cold air delivery pipes are aligned with the rear outer ring blades 32. The rear end cool air nozzles 50 of the cool air delivery pipes are respectively arranged at the rear of the air delivery pipes 16 as shown in fig. 9, so that the outer ring blades 32 blown by the high Wen Zuogong fuel gas cannot overheat.

Claims

1. Jet-propelled split-flow type rotor supercharged gas turbine comprises a gas compressor (21) and a turbine (23) connected through a crankshaft, wherein a rotor (25) with a plurality of rows of combustion chambers (26) is arranged between the gas compressor and the turbine, the rotor is arranged in a rotor shell (29), a plurality of equal distribution angle areas (40) are divided on the rotor shell (29), a ventilation inlet (8) and a ventilation outlet (7) which are positioned in the same angle are sequentially arranged from the starting position in each distribution angle area (40) on the rotor shell (29) to the tail end position in the rotating direction of the downstream rotor (25), an ignition cavity (31) with a spark plug (30), a first gas outlet (1), a second gas outlet (2), a third gas outlet (3), a fourth gas outlet (4) and a fifth gas outlet (5) … … are sequentially formed after the ventilation inlet and the ventilation outlet, the gas outlet (7) and the corresponding gas outlet are respectively communicated with a corresponding gas outlet (37) on a nozzle plate in front of the turbine through a compressed air pipe (9), and the jet-propelled split-flow type rotor supercharged gas turbine is characterized in that: after the first air outlet (1) in each air distribution angle area (40) is communicated with the first air delivery pipe (11), the rear side of the first air delivery pipe extends backwards through the turbine shell from the periphery of the turbine shell (24), high-temperature high-pressure working fuel gas sprayed out of the first air outlet (1) can be sprayed out backwards from the first air delivery pipe, and the second air outlet (2), the third air outlet (3), the fourth air outlet (4) and the fifth air outlet (5) … … after the first air outlet (1) are respectively communicated with corresponding air nozzles on a nozzle plate (37) in front of the turbine (23) through corresponding air delivery pipes.

2. The jet splitter rotor boost gas turbine of claim 1, wherein: after each first air delivery pipe (11) communicated with the first air outlet (1) in each air distribution angle zone (40) extends backwards to the turbine shell (24), the first air delivery pipe extends into the tail nozzle (19) at the rear part of the turbine shell, and the rear end of the first air delivery pipe (11) is communicated with the corresponding diffusion nozzle (20).

3. The jet splitter rotor boost gas turbine of claim 1, wherein: after each first air delivery pipe (11) communicated with the first air outlet (1) in each air distribution angle zone (40) extends backwards to pass through the turbine shell (24), the rear end of each first air delivery pipe is communicated with a diffusion nozzle (20) attached to the periphery of the tail nozzle (19).

4. The jet splitter rotor boost gas turbine of claim 1, wherein: after each first air delivery pipe (11) communicated with a first air outlet (1) in each air distribution angle area (40) extends backwards to the turbine shell (24), an air jet (38) is formed at the rear end of the first air delivery pipe (11), a final-stage blade (42) arranged at the rear side of the turbine (23) is positioned at the outer side of the turbine shell (24), the blade tops of the final-stage blades (42) are also connected with a connecting swivel (39) and the connecting swivel is positioned at the outer side of the turbine shell (24), the diameter size of the front end surface of the connecting swivel is the same as the diameter size of the rear end surface of the turbine shell (24), a double-acting outer ring blade (36) is formed at the periphery of the connecting swivel (39), the air jet (38) at the rear end of the first air delivery pipe (11) is aligned with an outer ring blade (36) connected with the periphery of the swivel (39), a fan duct (43) is arranged at the periphery of the outer ring blade, the fan duct is connected with the turbine shell (24) through a guide post piece (45), the double-acting outer ring blade (36) adopts a streamline section, a streamline center line (51) is basically a straight line and is provided with a thicker arc front surface (52), a windward surface (53) and a leeward surface (54) which extend backwards and are gradually thinned slightly, high-temperature high-pressure working fuel gas sprayed from the air jet (38) at the rear end of the first air delivery pipe blows the outer ring blade (36) to enable the outer ring blade to play a role of a turbine, after the outer ring blades rotate through the air jet ports, the outer ring blades can pressurize and discharge air flow entering from the front side of the fan duct (43) to the rear, and the outer ring blades can play a role of a fan.

5. The jet splitter rotor boost gas turbine of claim 4, wherein: when the double-acting outer ring blades (36) are made into longer sizes, the corresponding air jet ports (38) at the rear side of each first air delivery pipe (11) are also in an oblong shape and are obliquely arranged relative to the axis of the turbine, one side of each oblong air jet port is far away from the axis, the other side of each oblong air jet port is close to the axis, the width occupied by each oblong air jet port (38) enables each air jet port to correspond to a plurality of outer ring blades (36), and the radial size of the flat narrow part of each air jet port (38) is smaller than the length of the outer ring blade (36) in the radial direction, so that the air flow which is blown by the outer ring blade rotating through the air jet port (38) can be blown to the root of the blade from the top of the blade.

6. Jet-propelled split-flow type rotor supercharged gas turbine comprises a gas compressor (21) and a turbine (23) connected through a crankshaft, wherein a rotor (25) with a plurality of rows of combustion chambers (26) is arranged between the gas compressor and the turbine, the rotor is arranged in a rotor shell (29), a plurality of equal distribution angle areas (40) are divided on the rotor shell (29), a ventilation inlet (8) and a ventilation outlet (7) which are positioned in the same angle are sequentially arranged from the starting position in each distribution angle area (40) on the rotor shell (29) to the tail end position in the rotating direction of the downstream rotor (25), an ignition cavity (31) with a spark plug (30), a first gas outlet (1), a second gas outlet (2), a third gas outlet (3), a fourth gas outlet (4) and a fifth gas outlet (5) … … are sequentially formed after the ventilation inlet and the ventilation outlet, the gas outlet (7) and the corresponding gas outlet are respectively communicated with a corresponding gas outlet (37) on a nozzle plate in front of the turbine through a compressed air pipe (9), and the jet-propelled split-flow type rotor supercharged gas turbine is characterized in that: last stage blades (42) arranged at the rear side of the turbine (23) are arranged at the outer side of the turbine shell (24), the blade tops of the last stage blades (42) are also connected with a peripheral connecting swivel (39), the connecting swivel is positioned at the rear of the turbine shell (24), the diameter size of the front end face of the connecting swivel is the same as that of the rear end face of the turbine shell (24), peripheral outer ring blades (32) are also formed on the connecting swivel (39), a flaring turbine shell (27) covering the outer ring blades is arranged at the periphery of the outer ring blades, the flaring turbine shell is connected with the rear side of the turbine shell (24) through a baffle ring (28), a first air outlet (1) in each air distribution angle zone (40) and two air outlets at the middle and final positions are respectively extended backwards along the periphery of the turbine shell (24) through respective air distribution pipes, air distribution ports (38) are formed at the rear end of each air distribution pipe, the air distribution ports at the rear end of each air distribution pipe penetrate through the baffle ring (28) between the flaring shell (27) and the turbine shell (24), the air distribution ports at the rear end face of each air distribution angle zone (40) are aligned with the rear of the corresponding blade (27) of the turbine shell, and the air distribution ports (24) at the rear end face of each air distribution pipe, and the air distribution port (24) are arranged at a higher angle than the air distribution port (1) and the air distribution port at the rear end of each air distribution port outlet zone (air distribution end, and the air distribution port outlet zone (air distribution port) is arranged at the air outlet end, and the air distribution port outlet end, and air distribution port outlet end is respectively, the rest air outlets are respectively communicated with corresponding air nozzles on a nozzle plate (37) in front of the turbine (23) through corresponding air delivery pipes.

7. The jet splitter rotor boost gas turbine of claim 6, wherein: cold air delivery pipes (48) provided with intercoolers (49) are respectively led out from each compressed air delivery pipe (9) behind the air compressor (21), the number of the cold air delivery pipes is the same as that of the distribution angle areas (40) on the rotor shell, cold air spraying ports (50) are also formed at the rear ends of the cold air delivery pipes, and after the cold air delivery pipes (48) are uniformly distributed among other air delivery pipes and pass through baffle rings (28) which are connected with the flaring turbine shell (27) and the turbine shell (24), the cold air spraying ports (50) at the rear ends of the cold air delivery pipes are aligned with the outer ring blades (32) behind.

8. The jet splitter rotor boost gas turbine of claim 6 or 7, wherein: the last stage blades (42) and the integrally connected outer ring blades (32) at the rear side of the turbine (23) can be mounted on both the rotor body (33) of the turbine (23) and on a separate rotor disk (34) on the power take-off shaft (35).

9. Jet-propelled split-flow type rotor supercharged gas turbine comprises a gas compressor (21) and a turbine (23) connected through a crankshaft, wherein a rotor (25) with a plurality of rows of combustion chambers (26) is arranged between the gas compressor and the turbine, the rotor is arranged in a rotor shell (29), a plurality of equal distribution angle areas (40) are divided on the rotor shell (29), a ventilation inlet (8) and a ventilation outlet (7) which are positioned in the same angle are sequentially arranged from the starting position in each distribution angle area (40) on the rotor shell (29) to the tail end position in the rotating direction of the downstream rotor (25), an ignition cavity (31) with a spark plug (30), a first gas outlet (1), a second gas outlet (2), a third gas outlet (3), a fourth gas outlet (4) and a fifth gas outlet (5) … … are sequentially formed after the ventilation inlet and the ventilation outlet, the gas outlet (7) and the corresponding gas outlet are respectively communicated with a corresponding gas outlet (37) on a nozzle plate in front of the turbine through a compressed air pipe (9), and the jet-propelled split-flow type rotor supercharged gas turbine is characterized in that: last stage blades (42) arranged at the rear side of the turbine (23) are positioned at the outer side of the turbine shell (24), the blade tops of the last stage blades (42) are connected with a connecting swivel (39), the connecting swivel is positioned at the rear side of the turbine shell (24), the diameter size of the front end face of the connecting swivel is the same as that of the rear end face of the turbine shell (24), peripheral outer ring blades (32) are formed on the connecting swivel (39), peripheral connecting outer rings (41) are also formed at the blade tops of the outer ring blades (32), fan blades (44) are also formed on the connecting outer rings, a nozzle shell (46) is arranged at the periphery of the rear side of the turbine shell (24), the rear side of the turbine shell (24) is connected with the rear side of the nozzle shell (46) arranged at the periphery through a baffle ring (28), the diameter size of the rear end face of the nozzle shell (46) is the same as that of the rear connecting outer ring (41) provided with blades, a fan duct (43) covering the fan blades therein is also arranged at the periphery of the fan duct (44), the fan duct is connected with the air outlet ports (40) through a guide piece (45) to the respective air outlet ports (40) at the respective angles of the rear end of the turbine shell (24) and the air outlet port (24) through the middle part of the two air outlet ports (1), the air jet ports (38) formed at the rear ends of the air delivery pipes penetrate through baffle rings (28) between the nozzle shell (46) and the turbine shell (24), the rear outer ring blades (32) are aligned, the air jet ports at the rear ends of the air delivery pipes are wide in size, the air jet ports (38) can be fully arranged in an annular air jet port arrangement space between the nozzle shell (46) and the turbine shell (24), the rest air outlet ports except for a first air outlet port (1) and two air outlet ports at the middle and final positions in each air distribution angle area (40) are communicated with corresponding air jet ports on a nozzle disc (37) in front of a turbine (23) through corresponding air delivery pipes, and a structure body consisting of a final stage blade (42), the outer ring blades (32) and fan blades (44) behind the turbine (23) is arranged between a rotor body (33) and a rear tail cone (47) of the turbine through bearings.

10. The jet splitter rotor boost gas turbine of claim 9, wherein: cold air delivery pipes (48) provided with intercoolers (49) are respectively led out from each compressed air delivery pipe (9) behind the air compressor (21), the number of the cold air delivery pipes is the same as that of the distribution angle areas (40) on the rotor shell, cold air spraying ports (50) are also formed at the rear ends of the cold air delivery pipes, and after the cold air delivery pipes (48) are uniformly distributed among other air delivery pipes and pass through baffle rings (28) which are connected with the nozzle shells (46) and the turbine shells (24), the cold air spraying ports (50) at the rear ends of the cold air delivery pipes are aligned with the rear outer ring blades (32).