CN1302201C - Heavy gas turbine - Google Patents
Heavy gas turbine Download PDFInfo
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- CN1302201C CN1302201C CNB031337430A CN03133743A CN1302201C CN 1302201 C CN1302201 C CN 1302201C CN B031337430 A CNB031337430 A CN B031337430A CN 03133743 A CN03133743 A CN 03133743A CN 1302201 C CN1302201 C CN 1302201C
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Abstract
The present invention relates to a heavy gas turbine which is composed of a gas inlet case, inlet adjustable guide blades, a gas compressor, a diffuser, a combustion chamber, a turbine and an exhaust case, wherein the inner casting and the outer casting of the gas inlet case and a support spoke for bearing force are integrally cast into a whole; the cases of the components are connected by axial bolts; the gas compressor and a turbine rotor are in disk-drum type structure, and are tightly connected by the axial bolts so as to form a drum type gas compressor-turbine rotor which supports on a front sliding type plain bearing and a back sliding type plain bearing to form a double-support single-rotor structure; an output shaft positioned in the front is connected with a generator shaft through an elastic shaft coupler. The present invention is provided with the gas compressor with a high pressurization ratio, the combustion chamber with dry low-pollution emission, and the multi-stage air-cooled turbine bearing higher gas temperature, and has the advantages of light corresponding mass of the complete machine, and easy transportation.
Description
Technical field
The invention belongs to the dynamic power machine technical field, particularly a kind of power plant that are used for Gas Turbine Generating Units.
Background technique
Existing heavy duty gas turbine is all added these several big major components of inlet and outlet casing by gas compressor, firing chamber, turbine and is formed.Design, make a good heavy duty gas turbine, just require each critical piece to have higher performance, stable operating range.Require gas compressor to have high pressure ratio, high compressor efficiency, particularly higher level pressure ratio, and certain stable operation nargin is arranged; Require the firing chamber under all states of combustion machine operation, when changing with duty parameter, poor burning be can not cause and combustion stability and completeness of combustion influenced, can not allow under some state, the poor degree that burns is not enough, and the NOx content in the gas emission thing is increased, and therefore require firing chamber appropriate coupling, combination in nozzle and burning tissue, guarantee that the combustion machine can both keep efficient, stable burning and low NOx drainage in the range of operation of broad; Require turbine can reliablely and stablely work in higher fuel gas temperature, then turbine changes, stator blade must take multistage, reliable forced air cooling cooling, comprises that employing removes cooling air to cooled blade again after external cooling.Yet existing gas turbine is because the narrow limitation of critical piece technical performance and the coupling of global design cause its performance not necessarily fully up to expectations.
Summary of the invention
Situation at existing gas turbine the invention provides a kind of heavy duty gas turbine.
This heavy duty gas turbine, form by the main big parts such as return flow type connular combustor, multistage axial flow formula turbine and inlet and outlet casing that multiatage axial flow compressor, several burner inner liners are formed, constitute the structural type of a single rotor, dual-supporting, preceding output.
The return flow type connular combustor (9) that the present invention is made up of inlet casing (1), import variable vane (2), multiatage axial flow compressor (3), diffuser (8), a plurality of burner inner liner, multistage axial flow formula turbine (10) and exit casing critical pieces such as (11) are formed.
The inside and outside housing of inlet casing and the rectification support plate of some loads become one with cast inblock.Link with axial bolts between the casing of each parts, compressor rotor and turbine rotor all are dish drum structures, tightly link with axial bolts therebetween, gas compressor---the turbine rotor of forming a drum, be bearing on the plane bearing of former and later two sliding types, formed the single rotor structure of a dual-supporting, output shaft links by elastic coupling flexible coupling and generator shaft at front end.
Gas compressor of the present invention is made up of gas compressor stator and rotor, and the import variable vane is installed before the rotor, and gas compressor stator rectifier is made up of inner and outer rings and straightener(stator) blade etc.1～15 grade of wheel disc is installed on the rotor, 1～15 grade of compressor blade, drum barrel load dish after preceding axle journal and the two-stage, the rear end of its rotor and turbine rotor front end are connected to form a gas compressor---turbine integral rotor with axial bolts.
The adjustable inlet guide vane is housed before compressor inlet, on first and second grade casing inwall, is provided with processor casing structure, circumferentially be provided with several special-purpose skewed slots in I and II casing inwall upper edge respectively.It can improve the flow field of first and second level work blade tip air-flow of gas compressor, thereby enlarge the stable operation nargin of inlet, behind the 5th, 10 and 15 grades of gas compressors, be provided with air vent, and air bleed valve is housed, start venting, adjust the stable operation nargin that discharge quantity can enlarge the gas compressor off rating.
The stator casing of gas compressor, before and after being divided into two sections, front housing has level boundary that the limit is installed, and rear housing has vertical boundary that the limit is installed, and the characteristics of this structure can guarantee the rigidity basically identical of whole casing combination back level and Vertical direction, have strengthened the complete machine rigidity.
1～3 grade of dish of compressor rotor is designed to the cantilever type of protracting.4 grades of dishes and front axle collar are linked together the formation overall structure with axial bolts.5～10 grades of dish drums and two drum barrel stopping-off pieces of 11～15 grades of dish drums are the cell cube that electron beam welding is welded into.Link to each other with axial bolts between 1～4 grade of dish of rotor.Adopting radially respectively between 4 grades of dishes, 5～10 grades of dishes, three cell cubes of 11～15 grades of dishes, pin connects, on 1～15 grade of dish, 1～15 grade blade is housed, it is big characteristics of this gas compressor than it that rotor front axle constriction is gone into the length and the present heavy single-rotor gas turbine that have shortened rotor in 1～3 grade of dish greatly.Bolt, welding and the form of pin combination have radially been adopted in connection between the compressor rotor dish respectively, have made things convenient for the enforcement of rotor substep balance scheme, help improving balance quality of rotor, and the internal stress when reducing working rotor also is one of characteristics of this gas compressor.
For wheel disc and blade to turbine are carried cooling air, this programme adopts and does not carry different pressures to the turbine different fractions, the scheme of the cooling air of temperature is to improve the cooling effect to every grade of turbine wheel disc and blade, specific implementation method is the rotor internal cavity cooling air transmitting set that adopts radial air entraining pipe and layering sleeve pipe to form, cooling air is introduced from the drum barrel tapping, collect by several radial radiation shape air entraining pipes that are uniformly distributed along the circumference, the wheel disc and the blade that transfer to turbine along the layering sleeve pipe of inner chamber cool off them, this device rotates with compressor rotor with the inner radius that ring part is fixed on the compressor rotor wheel disc, the effect of radiation air entraining pipe is to reduce the cooling air that rotor internal cavity is drawn to heat up because of the wheel disc rotation effect, the cooling air that different pressures and temperature are isolated in the effect of layering sleeve pipe on the one hand forms passage, also play the effect of heat screen in addition, reduce radiative heat transfer cooling air.The characteristics of this technological scheme are, have overcome the not good enough shortcoming of cooling effect in the scheme of the sub-thread cooling air order cooling turbine wheel discs at different levels that adopt usually in the heavy combustion engine and blade.Adopt this device can increase substantially the cooling effect of what wheel disc and blade behind the cooling effect, particularly turbine.
Firing chamber of the present invention is made up of a plurality of divided combustions chamber (burner inner liner), be looped around the outside of gas compressor rear portion casing, neutral position at each divided combustion chamber head, the fuel-air premixed device (being dual fuel nozzle) that a fuel nozzle is set and is complementary with it, indoor at each divided combustion, lean premixed gas is finished combustion process with the mode of subregion sectional combustion, realize the discharging of low NOx and CO, one road fuel is drawn at the center of the fuel nozzle that mediates in each divided combustion chamber, this road fuel accounts for the sub-fraction that infeeds the whole fuel in firing chamber, it does not participate in the premix of air, thereby on the central position of each divided combustion chamber, formed the zone of combustion of the appropriate stoichiometric ratio of a part, guaranteed when hanging down poor operating mode, to become a stable burning things which may cause a fire disaster.
In each divided combustion chamber, by a plurality of dual-fuel fuel-air premixed devices, no matter make is that gas or liquid fuel all can be finished sufficient premixing with air, burning is finished in premixed fuel air Mixture subregion piecewise simultaneously, so just having realized that gas turbine can both keep infeeding the indoor fuel of divided combustion in very wide range of operation all can perfect combustion in certain oil-poor scope, thereby guarantee that gas turbine is not only at the nominal operation state, and under the non-specified running state of broad, can both keep high combustion stability and combustion efficiency and low disposal of pollutants.
Around the fuel-air premixed device that is provided with in each head of combustion chamber neutral position a plurality of fuel-air premixed devices are set, air obtains vortex power through the volution blade of premixed device, and fuel sprays into the zone of combustion after premixed device and air mixing.
At head of combustion chamber the air film wall being set separates the zone of combustion in fuel-air premixed device and downstream thereof, when combustion machine during in the work of little state, fuel consumption is less, for the poor oil firing in the zone of combustion is controlled in the oil-gas ratio scope of setting, to obtain stable burning and low disposal of pollutants, only in certain several fuel-air premixed device, supply fuel, therefore, burning is also only carried out in the zone of combustion in their downstreams, and the recirculating zone that fuel-air premixed device downstream forms keeps carrying out continuously of burning.
In order to guarantee fuel by perfect combustion, improve combustion efficiency, be provided with several flame stabilizers in the downstream of recirculating zone, form a recirculating zone in this device back, make unburnt fuel continue to finish burning.
Because burning is that subregion, segmentation are finished, in each district, section, finished the burning of part of fuel, so heat that fuel discharges in each section, the heat of once finishing (being regardless of section) burning rapidly and discharging is relatively low than concentrating, just the temperature of each zone of combustion is also relatively low, therefore help guaranteeing under the prerequisite of burning completely, obtaining lower disposal of pollutants.
Turbine of the present invention is to fasten at turbine engine dish drum axle, be provided with the working blade group successively, every group has some is to link to each other with dish drum axle, turbine working blade because of fir shape tenon tooth, on the turbine engine cylinder body, be provided with the nozzle blade group between per two groups of working blades, every group has some nozzle blades that link to each other with the turbine cylinder body; Turbine working blades at different levels all are fixed on dish drum axle with fir-shaped mortise and fasten, and its blade listrium inner and outer surface is as the hot air flow flow path boundary; The nozzle blade curtain plate is fixed on by two fulcrums to be installed on the limit in the turbine cylinder body, this listrium inner and outer surface is as the hot air flow flow path boundary, the momentum conversion of the working medium of turbine working blade by flowing through turbine engine drives turbine rotor, and nozzle blade is used for the mobile of working medium between per two working blades led.
For making the working medium temperature that gas turbine flows out from the firing chamber reach 1200 ℃～1300 ℃, increase the combustion acc power, each blade of turbine engine can work well again, and the life-span is long, for this reason, must use the cooling air cooling to some turbine working blades and nozzle blade, the former grade blades of the present invention adopt combined type cooling blade, I level nozzle blade wherein, the blade inner chamber is provided with guide plate and flat board, constitute dual-chamber structure, guide plate blade back direction, leaf basin direction all has the hole, and the blade inlet edge die cavity has air film hole, the blade back of blade, leaf basin inside is provided with radiating fin along leaf different spacing, and more and more littler along working medium flow direction radiating fin spacing, the adjacent therewith long matrix type groove of the eddy current with different intersection angles that also is provided with successively, the eddy current with different intersection angles of turbulence columns is lacked the matrix type groove; Leading edge cavity is provided with radially interrupted muscle in the turbine working blade, be provided with partition wall between leaf basin blade back, partition wall leaf basin blade back inwall between left and right in inferior road is provided with different angle and discrete rib, on leaf basin blade back inwall, be provided with the long matrix type groove of eddy current of different intersection angles and spacing successively, short matrix type groove of eddy current and the short matrix type groove of eddy current with turbulence columns.During work, its cooling air mobile is that the cooling air from the two strands of air-flows in firing chamber enters guide vane by the lower end, part cooling air enters the leading edge die cavity by the hole on the flat board, air film hole through leading edge carries out air film convection current cooling to the blade leading edge again, the hole of another part air on guide plate blade back direction enters the radiating fin along leaf different spacing, hole on the leaf basin direction enters the radiating fin along leaf different spacing, the air that comes out thus enters long and short eddy current matrix type groove, flow out by exhaust side seam crack at last, enter the working medium sprue; The 2nd, the cooled air stream of external water cooler of hanging oneself enters the center piping of dish drum axle system through outer conduit, inflow dish hole successively after the supercharging, root of blade variable cross section passage, the radially interrupted muscle of cooled blade leading edge, after the partition wall throttling, flow through leaf basin blade back different angle and discrete rib flow into the working medium sprue from exhaust gap behind the long and short eddy current matrix type groove.
Adopt each big parts of said structure technical characteristics, the heavy duty gas turbine that is combined into has the gas compressor than high supercharging pressure level; The fuel chamber of dried low pollution emission; Can bear the multistage air cooled turbine of higher fuel gas temperature, and be the heavy duty gas turbine of a mid power that relative mass is lighter in heavy duty gas turbine (110000kw), although the clean quality of complete machine is not leading indicator for heavy combustion engine, but for long-distance transport, particularly transport to the remote mountain areas, in the combustion machine with constant power, the lighter weight convenient transportation just shows its advantage.
Description of drawings
Fig. 1 is an overall structure schematic representation of the present invention;
Fig. 2 is the structural representation of gas compressor of the present invention;
Fig. 3 is the structural representation of firing chamber of the present invention;
Fig. 4 is divided combustion chamber head construction schematic representation in the firing chamber of the present invention;
Fig. 5 is a firing chamber of the present invention set air pre-mixing device structural representation;
Fig. 6 is the structural representation of divided combustion chamber in the firing chamber of the present invention;
Fig. 7 is a turbine structural representation of the present invention;
Fig. 8 is a turbine cooling flowing path schematic representation of the present invention;
Among the figure: 1 inlet casing, 2 import variable vanes, 3 gas compressors, axle journal before 4,5 radial air entraining pipes, 6 dual fuel nozzles, 7 burner inner liners, 8 diffusers, 9 connular combustors, 10 turbines, 11 exit casings, 12 back axle journals, 13 center pipings, 14 processor boxes, 15 gas compressor straightener(stator) blades, 16 gas compressor working blades, 17 compressor rotors, 18 wheel discs, 19 air vents, 20 nozzle blades, 21 layering sleeve pipes, 22 back drum barrel load dishes, 1～3 grade of dish of 23 gas compressors, 24 dish drum axle systems, 5～10 grades of dishes of 25 gas compressors, 26 drum barrel tappings, 27 11～15 grades of dishes, 28 gas compressor stator casings, 29 turbine rotors, divided combustion chambers 30,31 firing chambers, 32 outer wall of combustion chamber, 33 fuel-air premixed devices, 34 divided combustion chamber outer walls, 35 air film walls, 36 stabilizers, 37 center fuel nozzles, 38-42 divides each zone of combustion of section burning, 43 turbine working blades, 44 turbine engine cylinder bodies.
Embodiment
Overall structure of the present invention as shown in Figure 1, the critical pieces of being made up of inlet casing 1, import variable vane 2, multiatage axial flow compressor 3, diffuser 8, a plurality of burner inner liner such as return flow type connular combustor 9, multistage axial flow formula turbine 10 and exit casing 11 constitute.The rectification support plate cast inblock of the inner and outer shell of inlet casing 1 and 19 loads is an one, link with axial bolts between the casing of each parts, gas compressor 3 and turbine 10 are dish drum structure, tightly link with axial bolts therebetween, and form gas compressor---the turbine rotor of a drum, be bearing on the plane bearing of former and later two slips, be dual-supporting, single rotor structure.
Form by gas compressor stator (28) and compressor rotor (17).Import adjustable guide vane (2) is installed before the rotor, and gas compressor stator rectifier is made up of inner and outer rings and straightener(stator) blade (15).1～15 grade of wheel disc (18) is installed on the rotor, 1～15 grade of compressor blade (16), drum barrel load dish (22) after preceding axle journal (4) and the two-stage is connected to form a gas compressor---turbine integral rotor with axial bolts between compressor rotor rear end and turbine rotor front end.
The runner of gas compressor adopts advanced Pneumatic design method to determine.It is 14.7 that the optimum organization of this pneumatic design and blade type selecting makes it reach pressure ratio on the machine structure of 15 grades of gas compressors, and the efficient of design point reaches 0.84, and the average level pressure ratio reaches 1.196.
Gas compressor of the present invention has fully utilized the way of stable operation nargin under the various raising off working states.At compressor inlet adjustable inlet guide vane (2) is housed, on first and second grade casing inwall, is provided with processor casing structure (14), on wall, have several tilting sulculuses.It can improve the flow field of first and second level work blade tip air-flow of gas compressor, thereby enlarges the stable operation nargin of inlet.Design has air vent (19) on the 5th, 10 and 15 grades of outlet port outer walls of gas compressor, and adjustment starting discharge quantity can enlarge the stable operation nargin under the gas compressor off rating.
The stator casing (28) of gas compressor is divided into two sections of front and back.Front housing has the level boundary that the limit is installed, and rear housing has vertical boundary that the limit is installed, and this design feature can guarantee the rigidity basically identical of whole casing combination back level and Vertical direction, strengthens the complete machine rigidity.1～3 grade of dish of compressor rotor (23) is designed to the cantilever type of protracting, 4 grades of dishes are associated in electron beam welding with preceding axle journal (4) and form overall structure, are the cell cube that electron beam welding is welded between 5～10 grades of dish drums (25) and 11～15 grades of dish drums (27) and two drum barrel stopping-off pieces.1～4 grade of dish of rotor links to each other with axial bolts, adopts radially pin connection respectively between 4 grades of dishes, 5～10 grades of dishes and 11～17 grades of dish cell cubes.1～15 level work blade (16) is housed on 1～15 grade of dish.Rotor front axle constriction is gone into the length that has shortened rotor in 1～3 grade of dish greatly.
Be to carry cooling air to the wheel disc and the blade of turbine, this programme adopts to the turbine different fractions does not carry the scheme of cooling air of different pressures, temperature to improve the cooling effect of every grade of turbine wheel disc and blade.Specific implementation method is the rotor internal cavity cooling air transmitting set that adopts radial air entraining pipe (5) and layering sleeve pipe (21) to form.Cooling air is introduced from drum barrel tapping (26), is collected by several radial radiation shape air entraining pipes that are uniformly distributed along the circumference, and the wheel disc and the blade that transfer to turbine along the layering sleeve pipe of inner chamber cool off them.This device rotates with compressor rotor with the inner radius that ring part is fixed on the compressor rotor wheel disc.The effect of radiation air entraining pipe is to reduce the cooling air that rotor internal cavity is drawn to heat up because of the wheel disc rotation effect, the cooling air that different pressures and temperature are isolated in the effect of layering sleeve pipe on the one hand forms passage, also plays the radiative heat transfer of the effect minimizing of heat screen to cooling air in addition.
As shown in Figure 3, the endless tube type firing chamber that firing chamber of the present invention is made up of 20 burner inner liners, be looped around the outside of gas compressor rear portion casing, high-pressure air by the gas compressor outflow, behind diffuser, be back to the firing chamber, enter through swirler from the burner inner liner head, the fuel that sprays with nozzle oozes mixed, burning.Such structural type helps installing, overhauls, changes nozzle and burner inner liner, and has shortened gas compressor---the distance between two fulcrums of turbine rotor.
The head of each burner inner liner all has one group of three-flute combined type dual fuel nozzle, this group nozzle is by 1 three-flute combined type main fuel spray nozzle that occupy central authorities, form with 8 uniform on every side three-flute dual fuel nozzles, common constitute one group and can burn gaseous fuel---rock gas, can burn liquid fuel again---dual fuel nozzle of diesel oil, owing to adopted fuel premix technology, organize the technical measures of poor oil firing and sectional combustion rightly, make the content of products of combustion NOx in the combustion gas that the firing chamber discharges:
When using gas fuel, be no more than 50mg/Nm
3
During with liquid fuel (diesel oil), be no more than 250mg/Nm
3
Turbine of the present invention is 4 grades of axial flow turbomachines.
In 4 grades of axial turbine, I, II level work blade and I, II, III level guide vane are ventilation type, to guarantee to bear higher fuel gas temperature.
Be cooling turbine working blade and guide vane fully reliably, draw pressurized air after gas compressor is not at the same level respectively by pipeline, there is purpose to remove to cool off corresponding turbine working blade and guide vane not at the same level, and unlike routine the pressurized air of impulse mechanism of qi, in the past order cooling turbine blade and dish at different levels backward.Such as, air outside casing behind 8 grades of the impulse mechanisms of qi goes to the tip of cooling turbine III level guide vane and III, IV level turbine blade, from compressor---and the inside of turbine rotor, by the pressurized air behind 7 grades of the dedicated pipe pass, remove to cool off the root of III, IV level turbine blade; Draw the pressurized air after 10 grades, remove to cool off the root of II level turbine working blade and III level guide vane: the pipeline that these are special-purpose, be installed in internal rotor, be synchronous operated with rotor.In addition, in order to improve cooling effect to turbine I level work blade and II level guide vane, special behind 15 grades of gas compressors, draw high-pressure air through external water cooler, air cooling is cooled to about 150 ℃, cause rotor center piping rotating boosting simultaneously by pipeline again, remove to cool off I level turbine dish, tenon tooth, blade and II level guide vane then.
Double cavity structure is adopted in the inside of I level guide vane, cooling blast forms the air film cooling through serpentine channel by aperture, cooling air is through being staggered, and the piping that differs in size forms the eddy current matrix, reaches more than 500 ℃ thereby the surface of I level guide vane is lowered the temperature effectively.
Claims (2)
1, a kind of heavy duty gas turbine, include inlet casing, the import variable vane, gas compressor, diffuser, the firing chamber, turbine and exit casing, in the inlet casing, the rectification support plate casting of frame and load becomes an integral body, link to each other with axial bolts between each parts casing, gas compressor and turbine rotor are dish drum structure, link to each other with axial bolts therebetween, gas compressor---the turbine rotor of forming a drum, before being bearing in, on the plane bearing of latter two sliding type, constitute the single rotor structure of a dual-supporting, output shaft is preceding, link by elastic coupling flexible coupling and generator shaft, it is characterized in that described gas compressor is 15 grades of axial flow compressors, adopt electron beam welding to be connected between dish at different levels and the drum, adopt axial bolts to connect between 1～4 grade of dish, 4 grades of dishes, 5～10 grades of dishes, adopting radially respectively between three cell cubes of 11～15 grades of dishes, pin connects, it is 1 years old, 2,3 grades of dish drums, preceding axle journal, 4 grades of dishes link into an integrated entity, before preceding 3 grades of dishes are bearing in cantilevered fashion on axle journal and the 4 grades of dishes, form cantilever structure, for alleviating the quality of cantilever, 1,2,3,4 grades of compressor blades are made by titanium alloy, at gas compressor the 5th, be provided with air vent after 10 and 15 grades, and the air bleed valve of exitting for starting is housed, 1,2 grades of casing internal face upper edges are axially arranged with some skewed slots and form processor casing structure; The can-annular combustion chamber that described firing chamber is made up of 20 burner inner liners, be looped around the outside of gas compressor rear portion casing, each burner inner liner head all has one group of three-flute combined type dual fuel nozzle, this group nozzle is by 1 three-flute combined type main fuel spray nozzle that occupy central authorities, form with 8 uniform around it three-flute dual fuel nozzles, constitute one group jointly and can burn the dual fuel nozzle that gaseous fuel can burn liquid fuel again; Described turbine is 4 grades of axial turbine, its I, II level work blade and I, II, III level guide vane are ventilation type, double cavity structure is adopted in the inside of turbine I level guide vane, cooling blast passes through serpentine channel, form the air film cooling through aperture, the cooling gas circuit is staggered, and the piping that differs in size forms the eddy current matrix.
2, heavy duty gas turbine according to claim 1, the type of cooling that it is characterized in that described 4 grades of turbines adopts the bleed cooling, it is the air behind 8 grades of the impulse mechanisms of qi outside casing, remove cooling turbine III level guide vane and III, the tip of IV level turbine blade, from gas compressor---the inside of turbine rotor, by the pressurized air behind 7 grades of the built-in dedicated pipe pass, remove to cool off III, the root of IV level turbine dish and blade, draw the root that pressurized air after 10 grades removes to cool off II level turbine dish and working blade and III level guide vane, its special-purpose pipeline is at internal rotor, with rotor run-in synchronism, the cooling of turbine I level dish and working blade and II level guide vane be after drawing 15 grades high-pressure air through external water cooler, cause the rotor center piping by pipeline again after cooling, remove to cool off I level turbine dish behind the rotating boosting simultaneously, tenon tooth, blade and II level guide vane.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB031337430A CN1302201C (en) | 2003-07-16 | 2003-07-16 | Heavy gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB031337430A CN1302201C (en) | 2003-07-16 | 2003-07-16 | Heavy gas turbine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN1474034A CN1474034A (en) | 2004-02-11 |
| CN1302201C true CN1302201C (en) | 2007-02-28 |
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| CNB031337430A Expired - Lifetime CN1302201C (en) | 2003-07-16 | 2003-07-16 | Heavy gas turbine |
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| DE102004014117A1 (en) * | 2004-03-23 | 2005-10-13 | Alstom Technology Ltd | Component of a turbomachine with a cooling arrangement |
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| CN112523867A (en) * | 2020-12-17 | 2021-03-19 | 夏前锦 | Novel bridge type double-drum gas turbine |
| CN112944395B (en) * | 2021-05-12 | 2021-09-07 | 成都中科翼能科技有限公司 | Combined premixer for gas turbine |
| CN113834095B (en) * | 2021-11-02 | 2023-02-07 | 西安热工研究院有限公司 | Gas turbine annular tube type combustion chamber based on detonation combustion |
| CN113977061B (en) * | 2021-12-03 | 2023-01-31 | 中国航发燃气轮机有限公司 | Method for guaranteeing electron beam welding coaxiality of large-diameter drum barrel of gas turbine |
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|---|---|---|---|---|
| CN1034259A (en) * | 1988-01-14 | 1989-07-26 | 通用电气公司 | The bimodal swirler injector that is used for gas-turbine combustion chamber |
| CN1069561A (en) * | 1991-08-12 | 1993-03-03 | 通用电气公司 | The fuel supply system of double annular combustion chamber |
| CN1127327A (en) * | 1994-10-01 | 1996-07-24 | Abb管理有限公司 | Method and apparatus for sealing and cooling gas discharging side axle of axial gas turbine |
| CN1417462A (en) * | 2001-10-31 | 2003-05-14 | 通用电气公司 | Cooling system for gas turbine |
| CN2532242Y (en) * | 2002-01-10 | 2003-01-22 | 武汉三维汽轮电机股份有限公司 | Flow structure for small and intermediate sized turbine set |
Also Published As
| Publication number | Publication date |
|---|---|
| CN1474034A (en) | 2004-02-11 |
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Address after: 110043 Dong TA street, Dadong District, Shenyang, Liaoning Province, No. 6 Patentee after: AECC SHENYANG LIMING AERO-ENGINE Co.,Ltd. Address before: 110043 Dong TA street, Dadong District, Shenyang, Liaoning Province, No. 6 Patentee before: Aecc Shenyang Liming Aero Engine Co., Ltd. |
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