CN115324770A - Hydrogen fuel gas turbine engine - Google Patents
Hydrogen fuel gas turbine engine Download PDFInfo
- Publication number
- CN115324770A CN115324770A CN202211069466.8A CN202211069466A CN115324770A CN 115324770 A CN115324770 A CN 115324770A CN 202211069466 A CN202211069466 A CN 202211069466A CN 115324770 A CN115324770 A CN 115324770A
- Authority
- CN
- China
- Prior art keywords
- hydrogen
- combustion chamber
- turbine engine
- outlet
- gas turbine
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 title claims abstract description 70
- 239000001257 hydrogen Substances 0.000 title claims abstract description 70
- 229910052739 hydrogen Inorganic materials 0.000 title claims abstract description 70
- 239000002737 fuel gas Substances 0.000 title abstract description 16
- 230000007246 mechanism Effects 0.000 claims abstract description 73
- 239000007789 gas Substances 0.000 claims abstract description 51
- 238000002485 combustion reaction Methods 0.000 claims abstract description 46
- 239000007788 liquid Substances 0.000 claims abstract description 27
- 239000007921 spray Substances 0.000 claims abstract description 16
- 230000000087 stabilizing effect Effects 0.000 claims description 22
- 230000001914 calming effect Effects 0.000 claims description 2
- 230000008676 import Effects 0.000 claims description 2
- 230000006641 stabilisation Effects 0.000 claims 1
- 238000011105 stabilization Methods 0.000 claims 1
- 230000006835 compression Effects 0.000 abstract description 3
- 238000007906 compression Methods 0.000 abstract description 3
- 230000001133 acceleration Effects 0.000 abstract description 2
- 238000002347 injection Methods 0.000 abstract description 2
- 239000007924 injection Substances 0.000 abstract description 2
- 239000000446 fuel Substances 0.000 description 4
- MWUXSHHQAYIFBG-UHFFFAOYSA-N nitrogen oxide Inorganic materials O=[N] MWUXSHHQAYIFBG-UHFFFAOYSA-N 0.000 description 3
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 2
- CURLTUGMZLYLDI-UHFFFAOYSA-N Carbon dioxide Chemical compound O=C=O CURLTUGMZLYLDI-UHFFFAOYSA-N 0.000 description 2
- 229910052799 carbon Inorganic materials 0.000 description 2
- 239000003350 kerosene Substances 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 239000000243 solution Substances 0.000 description 2
- 239000004215 Carbon black (E152) Substances 0.000 description 1
- UGFAIRIUMAVXCW-UHFFFAOYSA-N Carbon monoxide Chemical compound [O+]#[C-] UGFAIRIUMAVXCW-UHFFFAOYSA-N 0.000 description 1
- 238000002679 ablation Methods 0.000 description 1
- 229910002092 carbon dioxide Inorganic materials 0.000 description 1
- 239000001569 carbon dioxide Substances 0.000 description 1
- 229910002091 carbon monoxide Inorganic materials 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000003912 environmental pollution Methods 0.000 description 1
- 229930195733 hydrocarbon Natural products 0.000 description 1
- 150000002430 hydrocarbons Chemical class 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000005855 radiation Effects 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/22—Fuel supply systems
- F02C7/224—Heating fuel before feeding to the burner
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/78—Other construction of jet pipes
- F02K1/82—Jet pipe walls, e.g. liners
- F02K1/822—Heat insulating structures or liners, cooling arrangements, e.g. post combustion liners; Infrared radiation suppressors
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Output Control And Ontrol Of Special Type Engine (AREA)
Abstract
The invention relates to the technical field of turbine engines, in particular to a hydrogen fuel gas turbine engine, which comprises: the gas injection device comprises a shell, wherein a gas compression mechanism, a combustion chamber, a turbine mechanism and a spray pipe mechanism are coaxially arranged in the shell in sequence; the first heat exchange structure is arranged in the air compressing mechanism and is provided with a first liquid hydrogen inlet, a first hydrogen outlet, an air inlet and an air outlet, the hydrogen outlet and the air outlet are communicated with the combustion chamber, liquid hydrogen and air enter the combustion chamber to be combusted after heat exchange in the first heat exchange structure, and the liquid hydrogen and air drive the turbine mechanism to do work and then are sprayed out after the acceleration of the spray pipe mechanism. The invention provides a hydrogen fuel gas turbine engine which has higher thermal efficiency and lower oil consumption and is environment-friendly.
Description
Technical Field
The invention relates to the technical field of turbine engines, in particular to a hydrogen fuel gas turbine engine.
Background
At present, most of aviation gas turbine engines adopt a Brayton cycle gas generator, air enters the engine from an air inlet of the engine, then the air flow passes through a low-pressure air compressor and a high-pressure air compressor in sequence and is compressed into high-pressure air flow with the pressure of more than 2Mpa, the high-pressure air flow enters a combustion chamber to be mixed with aviation kerosene and combusted, a large amount of heat is generated by combustion, high-temperature gas with the temperature of about 1600K is formed, the high-temperature gas enters a turbine and expands in a turbine channel, the turbine is driven to do work at the rotating speed of about 4 ten thousand revolutions per second at most, a part of turbine expansion work drives the air compressor to rotate, and a part of turbine expansion work is used for driving a propeller or a fan. Because each part in the gas turbine engine is in a high-temperature, high-pressure and high-speed working state, key parts such as a gas compressor, a combustion chamber, a turbine and the like are in a working limit state of materials, and the thermal efficiency of the engine is difficult to further improve by further improving thermodynamic cycle parameters of each part of the engine. Furthermore, as aviation kerosene C 12 H 23 Is a high hydrocarbon ratio fuel that is combusted in an aircraft gas turbine engine to produce large quantities of carbon dioxide and nitrogen oxides. Particularly, in the ground sliding state, fuel cannot be fully combusted in the engine due to the low-load operation state of the engine, so that the engine can emit a large amount of carbon monoxide which cannot be fully combusted, and the carbon emission can cause serious pollution to the environment.
Disclosure of Invention
Therefore, the technical problem to be solved by the invention is to overcome the defects of low thermal efficiency, high oil consumption rate and great environmental pollution of the gas turbine engine in the prior art, thereby providing a hydrogen fuel gas turbine engine which has high thermal efficiency, low oil consumption rate and is environment-friendly.
In order to solve the above technical problem, the present invention provides a hydrogen-fueled gas turbine engine including:
the gas injection device comprises a shell, wherein a gas compression mechanism, a combustion chamber, a turbine mechanism and a spray pipe mechanism are coaxially arranged in the shell in sequence;
the first heat exchange structure is arranged in the air compressing mechanism and is provided with a first liquid hydrogen inlet, a first hydrogen outlet, an air inlet and an air outlet, the hydrogen outlet and the air outlet are communicated with the combustion chamber, and liquid hydrogen and air enter the combustion chamber to be combusted after heat exchange in the first heat exchange structure and drive the turbine mechanism to do work and then are sprayed out after the acceleration of the spray pipe mechanism.
Optionally, a pressure stabilizing mechanism is arranged between the hydrogen outlet and the combustion chamber, and the hydrogen output from the hydrogen outlet enters the combustion chamber after being rectified and stabilized by the pressure stabilizing mechanism.
Optionally, the pressure stabilizing mechanism includes a pressure stabilizing chamber and a grid disposed in the pressure stabilizing chamber.
Optionally, the system further comprises a second heat exchange structure arranged in the spray pipe mechanism, the second heat exchange structure is provided with a second liquid hydrogen inlet, a second hydrogen outlet, a fuel gas inlet and a fuel gas outlet, and the second hydrogen outlet is communicated with the pressure stabilizing mechanism.
Optionally, the first heat exchange structure and the second heat exchange structure are both arranged on the inner wall of the shell in an annular direction.
Optionally, the air inlet and the air outlet are a plurality of first openings formed in the first heat exchange structure facing the inside of the housing, and the gas inlet and the gas outlet are a plurality of second openings formed in the second heat exchange structure facing the inside of the housing.
Optionally, the air compressing mechanism includes a centrifugal compressor, a centrifugal impeller and a diffuser, which are sequentially arranged, and the diffuser is communicated with the combustion chamber.
Optionally, an annular combustion chamber is arranged in the combustion chamber, and an inlet of the annular combustion chamber is communicated with the pressure stabilizing mechanism through a nozzle structure.
Optionally, the turbine mechanism comprises a guide structure communicating with the annular combustion chamber and a turbine structure arranged coaxially with the centrifugal impeller.
Optionally, the nozzle mechanism includes an inner ring and an outer ring, a cavity is formed between the inner ring and the outer ring, the cavity is communicated with the turbine mechanism, and the second heat exchange structure is disposed on an inner wall of the outer ring.
The technical scheme of the invention has the following advantages:
1. according to the hydrogen fuel gas turbine engine provided by the invention, liquid hydrogen and air exchange heat in the first heat exchange structure, enter the combustion chamber for combustion, drive the turbine mechanism to do work, and are accelerated by the spray pipe mechanism and then sprayed out. Liquid hydrogen is used as fuel of the gas turbine engine, zero carbon emission is realized, and the pollution of engine tail gas to the environment is greatly reduced; and when the liquid hydrogen exchanges heat with the air, the temperature of the compressed air in the air compressing mechanism is reduced, so that the working efficiency of the air compressing mechanism is improved, and the overall oil consumption rate of the engine is reduced.
2. According to the hydrogen fuel gas turbine engine, the pressure stabilizing mechanism is arranged between the hydrogen outlet and the combustion chamber, so that stable and ordered conversion of liquid hydrogen to gaseous hydrogen is realized, stable combustion of the hydrogen in the combustion chamber is ensured, and stable power output and high-precision control of the engine are further realized.
3. According to the hydrogen fuel gas turbine engine, the second heat exchange structure in the spray pipe mechanism enables liquid hydrogen to exchange heat with gas output by the turbine mechanism, the temperature of the gas in the spray pipe mechanism and the temperature of the wall surface of the shell are reduced, infrared radiation signals of the spray pipe mechanism are reduced, the infrared stealth performance of the spray pipe mechanism is improved, and ablation of the spray pipe mechanism and an aircraft skin is avoided.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the embodiments or the prior art descriptions will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings can be obtained by those skilled in the art without creative efforts.
FIG. 1 is a schematic illustration of a hydrogen-fueled gas turbine engine provided by the present invention.
Description of the reference numerals:
1. a housing; 2. a combustion chamber; 3. a centrifugal compressor; 4. a centrifugal impeller; 5. a diffuser; 6. a blade; 7. a first heat exchange structure; 8. a first opening; 9. a pressure stabilizing chamber; 10. a grid; 11. an annular combustion chamber; 12. an inner ring channel; 13. an outer ring channel; 14. a nozzle structure; 15. a guide; 16. a main shaft; 17. a turbine disk; 18. a turbine blade; 19. an inner ring; 20. an outer ring; 21. a cavity; 22. a second heat exchange structure; 23. and a second opening.
Detailed Description
The technical solutions of the present invention will be described clearly and completely with reference to the accompanying drawings, and it should be understood that the described embodiments are some, but not all embodiments of the present invention. All other embodiments, which can be obtained by a person skilled in the art without making any creative effort based on the embodiments in the present invention, belong to the protection scope of the present invention.
In addition, the technical features involved in the different embodiments of the present invention described below may be combined with each other as long as they do not conflict with each other.
One embodiment of a hydrogen fueled gas turbine engine, as shown in fig. 1, is an aircraft gas turbine engine, for example, comprising a compressor mechanism, a combustor 2, a turbine mechanism, and a nozzle mechanism, all coaxially disposed in sequence within a housing 1. When the hydrogen fuel gas turbine engine runs, air is compressed into high-pressure gas in the compression mechanism, the high-pressure gas and hydrogen enter the combustion chamber together to be combusted to form high-temperature high-pressure gas, then the high-temperature high-pressure gas enters the turbine mechanism to be expanded to do work, and the high-temperature high-pressure gas is accelerated by the spray pipe mechanism to generate forward thrust to be sprayed out.
The air compressing mechanism comprises a centrifugal compressor 3, a centrifugal impeller 4 and a diffuser 5 which are sequentially arranged, and blades 6 are arranged at the front end of the centrifugal impeller 4. First heat transfer structure 7 ring is located in the quick-witted casket of mechanism of calming anger front end, first heat transfer structure 7 is equipped with first liquid hydrogen import, first hydrogen export, air intlet and air outlet are for locating first heat transfer structure 7 orientation a plurality of first trompils 8 of casing 1 inside, the diameter of first trompil 8 is 0.3-1mm, the air outlet warp diffuser 5 with combustion chamber 2 intercommunication. Air enters the air compressing mechanism from an engine inlet, one part of the air enters the first heat exchange structure 7 through the air inlet, exchanges heat with liquid hydrogen entering from the first liquid hydrogen inlet, is output through the air outlet, is compressed with the other part of the air sequentially through the centrifugal impeller 4 to form high-pressure air flow, enters the diffuser 5 to be diffused and leave the air compressing mechanism, and enters the combustion chamber 2 together with hydrogen output from the first hydrogen outlet to be combusted.
And a pressure stabilizing mechanism is also arranged between the hydrogen outlet and the combustion chamber 2, and the pressure stabilizing mechanism comprises a pressure stabilizing chamber 9 and a grid 10 arranged in the pressure stabilizing chamber 9. The hydrogen output from the hydrogen outlet enters the combustion chamber 2 after being rectified and stabilized by the pressure stabilizing mechanism.
An annular combustion cavity 11 is arranged in the combustion chamber 2, an inner annular channel 12 and an outer annular channel 13 are formed between the annular combustion cavity 11 and the shell 1, and an inlet of the annular combustion cavity 11 is communicated with the pressure stabilizing mechanism through a nozzle structure 14. The nozzle arrangement 14 is 10-30 nozzles.
The turbine mechanism comprises a guide structure communicated with the annular combustion chamber 11 and a turbine structure coaxially arranged with the centrifugal impeller 4. The guiding structure is a guide 15 arranged at the outlet of the annular combustion chamber 11. The turbine structure includes a turbine disk 17 integrally connected to the centrifugal impeller 4 through the main shaft 16 of the engine, and turbine blades 18 provided on the turbine disk 17. The high-temperature gas expands in the passage of the turbine blade 18 to do work, the gas turbine disc 17 is driven to rotate, and the gas turbine disc 17 further drives the centrifugal impeller 4 to rotate.
The nozzle mechanism comprises an inner ring 19 and an outer ring 20, a cavity 21 is formed between the inner ring 19 and the outer ring 20, the cavity 21 is communicated with the turbine mechanism, the outer ring 20 is of a double-layer wall structure, and the second heat exchange structure 22 is annularly arranged on the inner wall of the outer ring 20. The second heat exchange structure 22 is provided with a second liquid hydrogen inlet, a second hydrogen outlet, a fuel gas inlet and a fuel gas outlet, the second hydrogen outlet is communicated with the pressure stabilizing mechanism, the fuel gas inlet and the fuel gas outlet are a plurality of second openings 23 which are arranged in the second heat exchange structure 22 and face the inner part of the shell 1, and the diameter of each second opening 23 is 0.3-1mm. The gas output by the turbine mechanism enters the second heat exchange structure 22 through the second opening 23, exchanges heat with the liquid hydrogen entering from the second liquid hydrogen inlet, the liquid hydrogen enters the pressure stabilizing mechanism through the second hydrogen outlet after exchanging heat and is burnt, and the gas after exchanging heat is discharged out of the spray pipe mechanism.
When the engine is started, liquid hydrogen enters the first heat exchange structure 7 and the second heat exchange structure 22 from the fuel storage tank respectively, air enters the air compressing mechanism from the engine inlet, one part of air enters the first heat exchange structure 7 through the air inlet, exchanges heat with the liquid hydrogen entering from the first liquid hydrogen inlet, is output through the air outlet, is compressed into high-pressure air flow with the other part of air sequentially through the centrifugal impeller 4, enters the diffuser 5 for pressure expansion and leaves the air compressing mechanism, and the hydrogen output from the first hydrogen outlet is subjected to pressure reduction through the pressure stabilizing mechanism and then enters the combustion chamber 2 together with the compressed air for combustion. The high-temperature gas expands in the passage of the turbine blade 18 to do work, the gas turbine disc 17 is driven to rotate, and the gas turbine disc 17 further drives the centrifugal impeller 4 to rotate. The gas output by the turbine mechanism enters the second heat exchange structure 22 through the second opening 23, exchanges heat with the liquid hydrogen entering from the second liquid hydrogen inlet, the liquid hydrogen enters the pressure stabilizing mechanism through the second hydrogen outlet after exchanging heat and is burnt, and the gas after exchanging heat is discharged out of the spray pipe mechanism.
It should be understood that the above examples are only for clarity of illustration and are not intended to limit the embodiments. Other variations and modifications will be apparent to persons skilled in the art in light of the above description. And are neither required nor exhaustive of all embodiments. And obvious variations or modifications therefrom are within the scope of the invention.
Claims (10)
1. A hydrogen-fueled gas turbine engine, comprising:
the gas-fired boiler comprises a shell (1), wherein a gas compressing mechanism, a combustion chamber (2), a turbine mechanism and a spray pipe mechanism are coaxially arranged in the shell (1) in sequence;
first heat transfer structure (7) is located in the mechanism of calming anger, first heat transfer structure (7) are equipped with first liquid hydrogen import, first hydrogen export, air intlet and air outlet, hydrogen export and air outlet all with combustion chamber (2) intercommunication, liquid hydrogen and air are in after the heat transfer in first heat transfer structure (7), get into combustion chamber (2) and burn to drive turbine mechanism does work, spout after spray tube mechanism accelerates again.
2. The hydrogen-fueled gas turbine engine according to claim 1, characterized in that a pressure stabilizing mechanism is provided between the hydrogen outlet and the combustion chamber (2), and the hydrogen output from the hydrogen outlet is rectified and stabilized by the pressure stabilizing mechanism and then enters the combustion chamber (2).
3. The hydrogen-fueled gas turbine engine according to claim 2, wherein the pressure stabilization mechanism includes a plenum (9) and a grill (10) disposed within the plenum (9).
4. The hydrogen-fueled gas turbine engine according to claim 2, further comprising a second heat exchanging structure (22) disposed in the nozzle mechanism, the second heat exchanging structure (22) being provided with a second liquid hydrogen inlet, a second hydrogen outlet, a gas inlet, and a gas outlet, the second hydrogen outlet being in communication with the pressure stabilizing mechanism.
5. The hydrogen-fueled gas turbine engine according to claim 4, characterized in that the first heat exchange structure (7) and the second heat exchange structure (22) are both circumferentially arranged on the inner wall of the casing (1).
6. The hydrogen-fueled gas turbine engine according to claim 4, characterized in that the air inlet and outlet are a plurality of first apertures (8) provided in the first heat exchanging structure (7) facing the inside of the casing (1), and the gas inlet and outlet are a plurality of second apertures (23) provided in the second heat exchanging structure (22) facing the inside of the casing (1).
7. The hydrogen-fueled gas turbine engine according to any one of claims 2 to 6, wherein the compressor mechanism comprises a centrifugal compressor (3), a centrifugal impeller (4) and a diffuser (5) arranged in this order, the diffuser (5) being in communication with the combustion chamber (2).
8. The hydrogen-fueled gas turbine engine according to claim 7, characterized in that an annular combustion chamber (11) is provided in the combustion chamber (2), the inlet of the annular combustion chamber (11) being in communication with the pressure-stabilizing means via a nozzle arrangement (14).
9. The hydrogen-fueled gas turbine engine according to claim 8, characterized in that the turbine mechanism comprises a guide structure communicating with the annular combustion chamber (11) and a turbine structure arranged coaxially with the centrifugal impeller (4).
10. The hydrogen-fueled gas turbine engine according to claim 5 or 6, wherein the nozzle means comprises an inner ring (19) and an outer ring (20), a cavity (21) being formed between the inner ring (19) and the outer ring (20), the cavity (21) being in communication with the turbine means, and the second heat exchanging structure (22) being provided on an inner wall of the outer ring (20).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211069466.8A CN115324770A (en) | 2022-08-31 | 2022-08-31 | Hydrogen fuel gas turbine engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211069466.8A CN115324770A (en) | 2022-08-31 | 2022-08-31 | Hydrogen fuel gas turbine engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115324770A true CN115324770A (en) | 2022-11-11 |
Family
ID=83929586
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211069466.8A Pending CN115324770A (en) | 2022-08-31 | 2022-08-31 | Hydrogen fuel gas turbine engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115324770A (en) |
-
2022
- 2022-08-31 CN CN202211069466.8A patent/CN115324770A/en active Pending
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| EP3623604B1 (en) | Hybrid expander cycle with pre-compression cooling and turbo-generator | |
| CN108757182B (en) | air-breathing rocket engine and hypersonic aircraft | |
| US6446425B1 (en) | Ramjet engine for power generation | |
| US20200200086A1 (en) | High speed propulsion system with inlet cooling | |
| CN106438104A (en) | Fuel-rich pre-burning turbofan engine | |
| CN114659138B (en) | Nozzle for combustion chamber, and gas turbine | |
| US11572840B2 (en) | Multi-mode combustion control for a rotating detonation combustion system | |
| JP7456082B2 (en) | Combustor nozzle, combustor, and gas turbine including the same | |
| CN115324770A (en) | Hydrogen fuel gas turbine engine | |
| CN114607525B (en) | Hydrogen fuel rotary ramjet turbofan engine | |
| US20030014960A1 (en) | Impulse turbine for rotary ramjet engine | |
| CN114607509A (en) | External rotor engine | |
| KR102415892B1 (en) | Micromixer and combustor having the same | |
| KR20200006149A (en) | Combustor and gas turbine including the same | |
| US20040016226A1 (en) | Radial impulse turbine for rotary ramjet engine | |
| CN216950579U (en) | Internal and external mixed combustion engine with combustion nozzle | |
| US11905914B2 (en) | Liquid hydrogen-liquid oxygen fueled powerplant | |
| KR102583224B1 (en) | Combustor with cluster and gas turbine including same | |
| CN216950580U (en) | Internal and external mixed combustion engine with combustion nozzle | |
| KR102583227B1 (en) | Combustor replaceable for each unit cluster and gas turbine including the same | |
| US11203972B2 (en) | Gas turbine and method of operating the same | |
| CN116428615B (en) | Circumferential circulation combustor between turbine stages | |
| KR102599921B1 (en) | Nozzle for combustor, combustor, and gas turbine including the same | |
| US20240310042A1 (en) | Injecting fuel-steam mixture into turbine engine combustor | |
| KR102619152B1 (en) | Nozzle for combustor, combustor, and gas turbine including the same |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |