CN116379474B - Thermal protection structure of fuel nozzle of aeroengine - Google Patents
Thermal protection structure of fuel nozzle of aeroengine Download PDFInfo
- Publication number
- CN116379474B CN116379474B CN202310153585.XA CN202310153585A CN116379474B CN 116379474 B CN116379474 B CN 116379474B CN 202310153585 A CN202310153585 A CN 202310153585A CN 116379474 B CN116379474 B CN 116379474B
- Authority
- CN
- China
- Prior art keywords
- heat shield
- nozzle
- fuel nozzle
- protection structure
- mounting flange
- 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.)
- Active
Links
- 239000000446 fuel Substances 0.000 title claims abstract description 55
- 238000003466 welding Methods 0.000 claims abstract description 26
- 238000007789 sealing Methods 0.000 claims description 17
- 230000003313 weakening effect Effects 0.000 claims description 17
- 230000000694 effects Effects 0.000 abstract description 7
- 238000010438 heat treatment Methods 0.000 abstract description 5
- 238000004939 coking Methods 0.000 abstract description 3
- 238000010030 laminating Methods 0.000 abstract 1
- 238000009413 insulation Methods 0.000 description 8
- 239000003921 oil Substances 0.000 description 8
- 238000002485 combustion reaction Methods 0.000 description 4
- 239000000295 fuel oil Substances 0.000 description 4
- 238000000034 method Methods 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 230000005855 radiation Effects 0.000 description 2
- 230000035882 stress Effects 0.000 description 2
- 238000000889 atomisation Methods 0.000 description 1
- 239000000571 coke Substances 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 230000008646 thermal stress Effects 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Nozzles For Spraying Of Liquid Fuel (AREA)
- Coke Industry (AREA)
Abstract
The application provides a thermal protection structure of an aeroengine fuel nozzle, which belongs to the technical field of aeroengines, and specifically comprises a heat shield, wherein the heat shield is wrapped at the part of the nozzle positioned in a casing, and is provided with an opening corresponding to the oil outlet end face of the nozzle; the welding boss is arranged on the outer wall of one end, close to the mounting flange, of the rod part, and one end, close to the mounting flange, of the heat shield is fixedly connected with the welding boss; the limiting bosses are arranged on the periphery of one end, close to the head, of the rod part, are arranged in a plurality, and are distributed along the circumferential direction of the rod part; the heat shield is close to and is equipped with a plurality of holes that weaken on the lateral wall of mounting flange one end, and the pole portion of nozzle is equipped with the seal ring in the one side that the hole was kept away from the welding boss that weakens, and seal ring and heat shield's inner wall laminating. Through the treatment scheme of this application, reduce the heating effect of fuel nozzle to the fuel in the internal passage, finally reduce the risk of fuel coking and nozzle jam.
Description
Technical Field
The application relates to the field of aeroengines, in particular to a thermal protection structure of a fuel nozzle of an aeroengine.
Background
The main combustion chamber fuel nozzle of an aircraft engine is generally arranged between the diffuser outlet and the combustor basket inlet, and has an approximate annular structure in cross section. When the engine works, fuel is supplied to the flame tube through the internal channel of the fuel nozzle to participate in combustion, the outer surface of the fuel nozzle is heated by high-temperature airflow at the outlet of the diffuser, and heat is transferred to the fuel flowing inside. The proper heating of the fuel oil by the gas at the outlet of the diffuser is beneficial to the atomization and combustion of the fuel oil under the small working condition, but the temperature of the inlet gas is too high under the large working condition, and the fuel oil is even heated to exceed the flash point temperature, so that the fuel oil is easy to coke and block the nozzle, and the performance of the engine is reduced.
Disclosure of Invention
In view of this, this application provides an aeroengine fuel nozzle thermal protection structure, has solved the problem among the prior art, reduces the heating effect of fuel nozzle to the fuel in the internal passage, finally reduces the risk of fuel coking and nozzle jam.
The application provides a thermal protection structure of aeroengine fuel nozzle adopts following technical scheme:
the utility model provides an aeroengine fuel nozzle thermal protection structure, the nozzle includes oil feed joint, mounting flange, pole portion and the head that sets gradually along the oil feed direction, the pole portion of nozzle is located inside the receiver, includes
The heat shield is wrapped at the part of the nozzle, which is positioned in the casing, and is provided with an opening corresponding to the oil outlet end face of the nozzle;
the welding boss is arranged on the outer wall of the rod part, which is close to one end of the mounting flange, and one end of the heat shield, which is close to the mounting flange, is fixedly connected with the welding boss;
the limiting bosses are arranged on the periphery of one end, close to the head, of the rod part, and are distributed along the circumferential direction of the rod part;
the side wall of the heat shield, which is close to one end of the mounting flange, is provided with a plurality of weakening holes, and the rod part of the nozzle is provided with a sealing ring at one side of the weakening holes, which is far away from the welding boss, and the sealing ring is attached to the inner wall of the heat shield.
Optionally, the gap between the heat shield and the rod portion is in the range of 0.5-2mm.
Optionally, the wall thickness of the heat shield ranges from 0.3 mm to 2mm.
Optionally, the outer profile of the heat shield matches the profile of the portion of the nozzle located inside the casing.
Optionally, the weakening hole is in a long strip shape extending along the length of the rod part, and the length range of the weakening hole is 5-30mm and the width is 1-3mm.
Optionally, the radial direction of the sealing ring is perpendicular to the length direction of the rod portion.
Optionally, a portion of the heat shield between adjacent ones of the weakened holes ranges from 1.5 mm to 2.5mm in length along the peripheral profile of the heat shield.
Optionally, the welding boss is parallel to the mounting flange, and the end face of the heat shield and the welding boss, which is close to one side of the mounting flange, is flush.
In summary, the present application includes the following beneficial technical effects:
an approximately-closed air heat insulation layer is formed between the heat shield and the fuel nozzle from the sealing ring to the nozzle head, so that the fuel nozzle is protected from convective heat transfer with high-temperature gas, radiation heat transfer by other surrounding components is avoided, and front heat transfer between the heat shield and the fuel nozzle is avoided. The heat protection structure is simple and novel, has high reliability, and can meet the heat protection requirement of the fuel nozzle of the main combustion chamber of the aero-engine
When the thermal-state working process is carried out, the heat shield formed by the two split structures is heated by high-temperature air flow, the temperature rise is carried out from the welding boss, the expansion is carried out along the length direction of the fuel nozzle rod part under the limit of the multi-position limiting boss of the fuel nozzle rod part, which is close to the nozzle head, the expansion is increased from the fuel nozzle head to the heat shield weakening hole in the direction perpendicular to the fuel nozzle rod, and the deformation uncoordinated stress caused by the temperature gradient between the fuel nozzle and the heat shield is eliminated through the deformation of the weak rigid structure between the sealing ring and the welding boss.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings that are needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present application, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a thermal protection structure of an aircraft engine fuel nozzle of the present application;
FIG. 2 is an exploded view of the fuel nozzle thermal protection structure of the aircraft engine of the present application;
FIG. 3 is a cross-sectional view of the fuel nozzle thermal protection structure of the aircraft engine of the present application.
Reference numerals illustrate: 1. a nozzle; 11. an oil inlet joint; 12. a mounting flange; 13. a stem portion; 14. a head; 2. a heat shield; 21. weakening the hole; 3. welding the boss; 4. a limit boss; 5. sealing the ring; 6. and a heat insulating layer.
Detailed Description
Embodiments of the present application are described in detail below with reference to the accompanying drawings.
Other advantages and effects of the present application will become apparent to those skilled in the art from the present disclosure, when the following description of the embodiments is taken in conjunction with the accompanying drawings. It will be apparent that the described embodiments are only some, but not all, of the embodiments of the present application. The present application may be embodied or carried out in other specific embodiments, and the details of the present application may be modified or changed from various points of view and applications without departing from the spirit of the present application. It should be noted that the following embodiments and features in the embodiments may be combined with each other without conflict. All other embodiments, which can be made by one of ordinary skill in the art based on the embodiments herein without making any inventive effort, are intended to be within the scope of the present application.
It is noted that various aspects of the embodiments are described below within the scope of the following claims. It should be apparent that the aspects described herein may be embodied in a wide variety of forms and that any specific structure and/or function described herein is merely illustrative. Based on the present application, one skilled in the art will appreciate that one aspect described herein may be implemented independently of any other aspect, and that two or more of these aspects may be combined in various ways. For example, an apparatus may be implemented and/or a method practiced using any number of the aspects set forth herein. In addition, such apparatus may be implemented and/or such methods practiced using other structure and/or functionality in addition to one or more of the aspects set forth herein.
It should also be noted that the illustrations provided in the following embodiments merely illustrate the basic concepts of the application by way of illustration, and only the components related to the application are shown in the drawings and are not drawn according to the number, shape and size of the components in actual implementation, and the form, number and proportion of the components in actual implementation may be arbitrarily changed, and the layout of the components may be more complicated.
In addition, in the following description, specific details are provided in order to provide a thorough understanding of the examples. However, it will be understood by those skilled in the art that the aspects may be practiced without these specific details.
The embodiment of the application provides a thermal protection structure of an aeroengine fuel nozzle.
As shown in fig. 1-3, the heat protection structure of the fuel nozzle 1 of the aeroengine is provided, the nozzle 1 comprises an oil inlet joint 11, a mounting flange 12, a rod part 13 and a head part 14 which are sequentially arranged along the oil inlet direction, the mounting flange 12 is used for being fixedly connected with the engine, the nozzle 1 is fixedly arranged on the engine, the oil inlet joint 11 is positioned outside the engine, and the rod part 13 and the head part 14 of the nozzle 1 are positioned inside a casing of the engine.
The thermal protection structure includes:
the heat shield 2 is wrapped at the part of the nozzle 1 positioned in the casing, and an opening corresponding to the oil outlet end face of the nozzle 1 is arranged on the heat shield 2. In one embodiment, the heat shield 2 is formed by butting two split structures in mirror symmetry, the symmetry line of the two split structures is along the length direction of the stem 13 of the nozzle 1, the symmetry plane of the split structures is parallel to the radial direction of the head 14, the nozzle itself is also in mirror symmetry, the symmetry line of the nozzle 1 is along the length direction of the stem 13, and along the radial direction of the head 14, the symmetry line also corresponds to the axis of the head 14, so to speak, the heat shield mirror symmetry plane coincides with the symmetry plane of the nozzle itself. After wrapping the nozzle 1 by the two split structures, the two split structures are then butt-jointed and fixed into a whole and welded on the outer side wall of the nozzle 1.
And the welding boss 3 is arranged on the outer wall of the rod part 13, which is close to one end of the mounting flange 12, and one end of the heat shield 2, which is close to the mounting flange 12, is fixedly connected with the welding boss 3 through welding.
The limiting bosses 4 are arranged on the periphery of one end, close to the head 14, of the rod 13, the limiting bosses 4 are arranged in a plurality, and are distributed along the circumferential direction of the rod 13, and the limiting bosses 4 are abutted against the inner wall of the heat shield 2.
The side wall of the heat shield 2, which is close to one end of the mounting flange 12, is provided with a plurality of weakening holes 21, one side of the weakening holes 21, which is far away from the welding boss 3, of the rod portion 13 of the nozzle 1 is provided with a sealing ring 5, and the sealing ring 5 is attached to the inner wall of the heat shield 2.
When the heat shield 2 works in a thermal state, the temperature of the heat shield 2 is increased by the heating action of high-temperature air flow, the heat shield 2 starts from the welding boss 3, stretches along the length direction of the rod part 13 of the fuel nozzle 1 under the limitation of a plurality of limiting bosses 4, expands from the head part 14 to the weakening holes 21 of the heat shield 2 in the direction perpendicular to the length of the rod part of the fuel nozzle 1, and deforms through the weak rigid structure between the sealing ring 5 and the welding boss 3 so as to eliminate the uncooled deformation stress between the fuel nozzle 1 and the heat shield 2 caused by the temperature gradient. At this time, an approximately closed air heat insulation layer 6 is formed between the heat shield 2 and the fuel nozzle 1 from the sealing ring 5 to the head 14 of the nozzle 1, so that the fuel nozzle 1 is protected from convective heat transfer with high-temperature gas, radiation heat transfer by other surrounding components is avoided, and front heat conduction between the heat shield 2 and the fuel nozzle 1 is avoided, so that the fuel nozzle 1 is small in heating use and low in temperature rise, less heat transferred from the fuel nozzle 1 to the fuel in an internal channel is finally ensured, and the risks of fuel coking and blockage of the nozzle 1 can be effectively reduced.
The gap between the heat shield 2 and the stem 13 is in the range of 0.5-2mm to minimize the outer profile of the heat shield 2 and to provide a suitable thickness of the air insulation 6.
The wall thickness of the heat shield 2 ranges from 0.3 to 2mm.
The outer contour of the heat shield 2 matches the contour of the part of the nozzle 1 located inside the casing.
The weakening hole 21 is in a strip shape extending along the length of the rod part 13, the length range of the weakening hole 21 is 5-30mm, the width is 1-3mm, the rigidity of the heat shield 2 at the position is weakened while the strength requirement is met, and the thermal deformation at the position is ensured to eliminate the thermal stress generated by the temperature gradient. The number of the weakening holes 21 is 2-10,
the radial direction of the sealing ring 5 is perpendicular to the length direction of the rod 13, wherein the radial direction of the sealing ring 5 is understood to be the end face of the sealing ring 5. The sealing ring 5 is of a full ring structure, and has a length of 1-3mm along the length direction of the rod portion 13 so as to form an upper sealing structure of the air heat insulation layer 6, and a radial height of 0.5-2m so as to support the heat insulation cover 2, provide a proper thickness of the air heat insulation layer 6 and reduce the heat conduction effect of the heat insulation cover 2 on the fuel nozzle 1. Radial height refers to the length of the side wall of the protruding stem 13.
The portion of the heat shield 2 between adjacent ones of the weakening holes 21 has a length along the circumferential profile of the heat shield 2 in the range of 1.5-2.5mm.
The welding boss 3 is parallel to the mounting flange 12, and the heat shield 2 and the end face of the welding boss 3 close to one side of the mounting flange 12 are flush. The welding boss 3 is of a full ring structure, and is as close to the mounting flange 12 of the upper end fuel nozzle 1 as possible, so that the fuel nozzle 1 is protected from heat to the greatest extent. The distance between the two end faces of the welding boss 3 is 2-6mm, so that the heat shield 2 is convenient to position and weld, and the heat conduction effect of the heat shield 2 on the fuel nozzle 1 is reduced as much as possible.
The limit bosses 4 are circumferentially distributed in 2-8, the distance along the length direction of the rod part 13 is 1-3mm, the radial height is 0.5-2mm, and the length along the circumferential direction of the rod part 13 is 1-3mm, so as to support the heat shield 2, provide a proper thickness of the air heat insulation layer 6 and reduce the heat conduction effect of the heat shield 2 on the fuel nozzle 1. Wherein the radial height refers to the length of the side wall of the protruding stem 13.
The foregoing is merely specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions easily conceivable by those skilled in the art within the technical scope of the present application should be covered in the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (8)
1. The utility model provides an aeroengine fuel nozzle heat protection structure, the nozzle includes oil feed joint, mounting flange, pole portion and the head that sets gradually along the oil feed direction, the pole portion of nozzle is located inside the receiver, its characterized in that includes
The heat shield is wrapped at the part of the nozzle, which is positioned in the casing, and is provided with an opening corresponding to the oil outlet end face of the nozzle;
the welding boss is arranged on the outer wall of the rod part, which is close to one end of the mounting flange, and one end of the heat shield, which is close to the mounting flange, is fixedly connected with the welding boss;
the limiting bosses are arranged on the periphery of one end, close to the head, of the rod part, and are distributed along the circumferential direction of the rod part;
the side wall of the heat shield, which is close to one end of the mounting flange, is provided with a plurality of weakening holes, and the rod part of the nozzle is provided with a sealing ring at one side of the weakening holes, which is far away from the welding boss, and the sealing ring is attached to the inner wall of the heat shield.
2. The aircraft engine fuel nozzle thermal protection structure of claim 1, wherein the gap between the heat shield and the stem is in the range of 0.5-2mm.
3. The aircraft engine fuel nozzle thermal protection structure of claim 1, wherein the heat shield has a wall thickness in the range of 0.3-2mm.
4. The aircraft engine fuel nozzle thermal protection structure of claim 1, wherein the outer profile of the heat shield matches the profile of the portion of the nozzle located inside the casing.
5. The aircraft engine fuel nozzle thermal protection structure of claim 1, wherein the weakening hole is elongated along the length of the shaft, and the weakening hole has a length ranging from 5mm to 30mm and a width ranging from 1 mm to 3mm.
6. The aircraft engine fuel nozzle thermal protection structure of claim 1, wherein the seal ring radial direction is perpendicular to the length direction of the stem.
7. The aircraft engine fuel nozzle thermal protection structure of claim 1, wherein a portion of said heat shield between adjacent said attenuation holes ranges from 1.5 mm to 2.5mm in length along a circumferential profile of said heat shield.
8. The aircraft engine fuel nozzle thermal protection structure of claim 1, wherein the welding boss is parallel to the mounting flange, and the heat shield and the welding boss are flush with an end face of a side of the mounting flange.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310153585.XA CN116379474B (en) | 2023-02-22 | 2023-02-22 | Thermal protection structure of fuel nozzle of aeroengine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310153585.XA CN116379474B (en) | 2023-02-22 | 2023-02-22 | Thermal protection structure of fuel nozzle of aeroengine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN116379474A CN116379474A (en) | 2023-07-04 |
| CN116379474B true CN116379474B (en) | 2024-04-16 |
Family
ID=86973928
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310153585.XA Active CN116379474B (en) | 2023-02-22 | 2023-02-22 | Thermal protection structure of fuel nozzle of aeroengine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116379474B (en) |
Citations (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2002061810A (en) * | 2000-08-18 | 2002-02-28 | Mitsubishi Electric Corp | Liquid fuel combustion device |
| CN204438198U (en) * | 2014-12-15 | 2015-07-01 | 中国燃气涡轮研究院 | A kind of jet stem portion thermal protection structure |
| CA2895409A1 (en) * | 2014-06-26 | 2015-12-26 | General Electric Company | Conical-flat heat shield for gas turbine engine combustor dome |
| CN105202577A (en) * | 2014-06-25 | 2015-12-30 | 中航商用航空发动机有限责任公司 | Fuel nozzle and combustor |
| EP2995859A1 (en) * | 2014-09-12 | 2016-03-16 | Siemens Aktiengesellschaft | Heat shield element for a heat shield of a combustion chamber |
| EP3354986A1 (en) * | 2017-01-30 | 2018-08-01 | Siemens Aktiengesellschaft | Fastening screw for a heat shield element |
| CN108488834A (en) * | 2018-03-07 | 2018-09-04 | 成都航利航空科技有限责任公司 | A kind of aero-engine fuel nozzle housing unit structure for increasing material and subtracting material manufacture |
| CN109506232A (en) * | 2018-11-16 | 2019-03-22 | 崔小勤 | A kind of burner and its method based on biomass boiler |
| CN110906364A (en) * | 2018-09-14 | 2020-03-24 | 安萨尔多能源公司 | Metal insulating brick for a combustion chamber of a gas turbine |
| CN111623376A (en) * | 2019-02-27 | 2020-09-04 | 三菱日立电力系统株式会社 | Gas turbine combustor and gas turbine |
| CN111981511A (en) * | 2020-07-31 | 2020-11-24 | 中国航发贵阳发动机设计研究所 | Fuel nozzle air heat insulation structure |
| JP2021135032A (en) * | 2020-02-28 | 2021-09-13 | 本田技研工業株式会社 | Fuel jet device for gas turbine |
| WO2021180349A1 (en) * | 2020-03-10 | 2021-09-16 | Siemens Aktiengesellschaft | Combustion chamber having a ceramic heat shield and seal |
| EP4043787A1 (en) * | 2021-02-11 | 2022-08-17 | Corten Art Doo Sabac | Biofireplace with automatic combustion control |
| EP4089265A1 (en) * | 2021-05-11 | 2022-11-16 | Honeywell International Inc. | Coating occlusion resistant effusion cooling holes for gas turbine engine |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CA2891128C (en) * | 2012-11-15 | 2017-06-13 | General Electric Company | Fuel nozzle heat shield |
-
2023
- 2023-02-22 CN CN202310153585.XA patent/CN116379474B/en active Active
Patent Citations (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2002061810A (en) * | 2000-08-18 | 2002-02-28 | Mitsubishi Electric Corp | Liquid fuel combustion device |
| CN105202577A (en) * | 2014-06-25 | 2015-12-30 | 中航商用航空发动机有限责任公司 | Fuel nozzle and combustor |
| CA2895409A1 (en) * | 2014-06-26 | 2015-12-26 | General Electric Company | Conical-flat heat shield for gas turbine engine combustor dome |
| EP2995859A1 (en) * | 2014-09-12 | 2016-03-16 | Siemens Aktiengesellschaft | Heat shield element for a heat shield of a combustion chamber |
| CN204438198U (en) * | 2014-12-15 | 2015-07-01 | 中国燃气涡轮研究院 | A kind of jet stem portion thermal protection structure |
| EP3354986A1 (en) * | 2017-01-30 | 2018-08-01 | Siemens Aktiengesellschaft | Fastening screw for a heat shield element |
| CN108488834A (en) * | 2018-03-07 | 2018-09-04 | 成都航利航空科技有限责任公司 | A kind of aero-engine fuel nozzle housing unit structure for increasing material and subtracting material manufacture |
| CN110906364A (en) * | 2018-09-14 | 2020-03-24 | 安萨尔多能源公司 | Metal insulating brick for a combustion chamber of a gas turbine |
| CN109506232A (en) * | 2018-11-16 | 2019-03-22 | 崔小勤 | A kind of burner and its method based on biomass boiler |
| CN111623376A (en) * | 2019-02-27 | 2020-09-04 | 三菱日立电力系统株式会社 | Gas turbine combustor and gas turbine |
| JP2021135032A (en) * | 2020-02-28 | 2021-09-13 | 本田技研工業株式会社 | Fuel jet device for gas turbine |
| WO2021180349A1 (en) * | 2020-03-10 | 2021-09-16 | Siemens Aktiengesellschaft | Combustion chamber having a ceramic heat shield and seal |
| CN111981511A (en) * | 2020-07-31 | 2020-11-24 | 中国航发贵阳发动机设计研究所 | Fuel nozzle air heat insulation structure |
| EP4043787A1 (en) * | 2021-02-11 | 2022-08-17 | Corten Art Doo Sabac | Biofireplace with automatic combustion control |
| EP4089265A1 (en) * | 2021-05-11 | 2022-11-16 | Honeywell International Inc. | Coating occlusion resistant effusion cooling holes for gas turbine engine |
Non-Patent Citations (1)
| Title |
|---|
| 近空间高超声速飞行器防热隔热与热力耦合研究进展;蒋持平;柴慧;严鹏;;力学与实践;20110208(01);5-13+38 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN116379474A (en) | 2023-07-04 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US8240151B2 (en) | Fuel injector nozzles for gas turbine engines | |
| JP4083717B2 (en) | Combustor insulation shield panel and combination of insulation shield panel and shell | |
| US9360217B2 (en) | Flow sleeve for a combustion module of a gas turbine | |
| JP4216052B2 (en) | Suppressive seal with thermal compliance | |
| US8181440B2 (en) | Arrangement of a semiconductor-type igniter plug in a gas turbine engine combustion chamber | |
| JP6431730B2 (en) | Internally cooled transition duct rear frame | |
| US8015816B2 (en) | Apparatus for discouraging fuel from entering the heat shield air cavity of a fuel injector | |
| US20140260273A1 (en) | Continuous combustion liner for a combustor of a gas turbine | |
| US20080253884A1 (en) | Out-flow margin protection for a gas turbine engine | |
| US7565807B2 (en) | Heat shield for a fuel manifold and method | |
| CA2604540C (en) | Reduced stress internal manifold heat shield attachment | |
| EP3315866B1 (en) | Combustor assembly with mounted auxiliary component | |
| CN103930725B (en) | The method of the multi fuel nozzle improved and amendment dual fuel nozzle | |
| US10928067B2 (en) | Double skin combustor | |
| EP2532836A2 (en) | Combustion liner and transistion piece | |
| CN116379474B (en) | Thermal protection structure of fuel nozzle of aeroengine | |
| US11828249B2 (en) | Exterior nozzle member for a turbomachine | |
| EP3339609A1 (en) | Mounting assembly for gas turbine engine fluid conduit | |
| CN110864326B (en) | Non-full-contact type nozzle heat-insulating cap, nozzle and design method | |
| US10982856B2 (en) | Fuel nozzle with sleeves for thermal protection | |
| JP7271232B2 (en) | Inner cooling shroud for annular combustor liner transition zone | |
| US20220074595A1 (en) | Turbomachine combustion chamber | |
| RU29122U1 (en) | Flame tube of a combustion chamber of a gas turbine engine |
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 | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |