CN115507392B - Connection structure of ceramic matrix composite flame tube and metal piece - Google Patents
Connection structure of ceramic matrix composite flame tube and metal piece Download PDFInfo
- Publication number
- CN115507392B CN115507392B CN202211133069.2A CN202211133069A CN115507392B CN 115507392 B CN115507392 B CN 115507392B CN 202211133069 A CN202211133069 A CN 202211133069A CN 115507392 B CN115507392 B CN 115507392B
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- China
- Prior art keywords
- metal
- ceramic matrix
- matrix composite
- flame tube
- metal piece
- Prior art date
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- 239000002184 metal Substances 0.000 title claims abstract description 92
- 239000011153 ceramic matrix composite Substances 0.000 title claims abstract description 59
- 238000001816 cooling Methods 0.000 claims abstract description 25
- 238000003466 welding Methods 0.000 claims abstract description 5
- 238000002485 combustion reaction Methods 0.000 claims description 16
- 239000000446 fuel Substances 0.000 claims description 4
- 238000002679 ablation Methods 0.000 abstract description 5
- 230000035882 stress Effects 0.000 description 15
- 239000002737 fuel gas Substances 0.000 description 6
- 239000007789 gas Substances 0.000 description 6
- 239000007769 metal material Substances 0.000 description 6
- 238000010586 diagram Methods 0.000 description 4
- 239000000463 material Substances 0.000 description 3
- 230000008646 thermal stress Effects 0.000 description 3
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 206010003591 Ataxia Diseases 0.000 description 1
- 206010010947 Coordination abnormal Diseases 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000012938 design process Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000001125 extrusion Methods 0.000 description 1
- 208000016290 incoordination Diseases 0.000 description 1
- 238000007789 sealing Methods 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
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/60—Support structures; Attaching or mounting means
-
- 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
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/14—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant
-
- 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
-
- 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
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
-
- 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)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses a connecting structure of a ceramic matrix composite flame tube and a metal piece, which comprises the following components: a metal piece; the metal piece comprises a metal runner mounting ring and an elastic supporting ring; the metal runner mounting ring is connected with the elastic supporting ring through welding; 3-30 air entraining grooves are formed in the left side of the metal runner mounting ring; and 3-40 stress release grooves are formed in the outer side of the elastic support ring. According to the invention, the L-shaped elastic support ring is provided with the stress release grooves, so that the elasticity of the structure can be effectively increased, and further, smaller stress in a high-temperature working state is realized, and the damage and failure of the ceramic matrix composite flame tube are avoided. The invention also provides a plurality of air entraining grooves on the metal runner mounting ring, which form a cooling air flow channel together with the stress releasing grooves, so that cooling air flow can be provided for the metal piece, and finally ablation failure of the downstream metal piece is avoided.
Description
Technical Field
The invention relates to the technical field of connection structures of aeroengines, in particular to a connection structure of a ceramic matrix composite flame tube and a metal piece.
Background
The aero-engine converts fuel into high-temperature fuel gas through a combustion process in a combustion chamber part to push a turbine to do work. The high temperature gas will flow through the combustion chamber and the flow path of the turbine and heat the parts that make up the gas flow path. In recent years, in order to improve the cycle efficiency and unit thrust of an aeroengine and further to make it more fuel-efficient and lighter, the temperature of high-temperature fuel gas is also being increased. Therefore, the parts of the flow channel contacting the high-temperature fuel gas in the combustion chamber and the turbine are required to be made of materials with high temperature resistance and effectively cooled.
The ceramic matrix composite material has higher temperature resistance and lower density than metal materials, and is one of internationally recognized aeroengine temperature resistant materials with great application prospect.
Ceramic matrix composites can be used for gas flow passages to withstand high temperatures, but given that ceramic matrix composites are less strong and more costly than metallic materials, aircraft engine non-flow passage elements still require a significant number of metallic parts. Therefore, a connection structure must exist between the ceramic matrix composite part and the metal part. The thermal expansion coefficient of the ceramic matrix composite is only about 1/4 of that of the metal part, so that the connecting structure is extremely easy to generate thermal deformation and incoordination at high temperature, and structural failure is caused.
The flame tube is a high temperature gas flow path member of the combustor assembly. The reflow flame tube is widely applied in small-sized vortex shaft aeroengines. As described above, to improve the temperature resistance of the reflow flame tube, a ceramic matrix composite is selected for processing. The outlet portion is also required to be connected to the associated non-runner metal part.
FIG. 1 is a schematic diagram of a conventional ceramic matrix composite and metal part connection structure, as shown in FIG. 1, with reference to a center line of rotation, the connection structure comprising: the combustion chamber comprises a combustion chamber casing, a ceramic matrix composite flame tube and a metal material connecting piece, wherein the combustion chamber casing is connected with the metal material connecting piece; the metal material connecting piece is connected with the ceramic matrix composite flame tube. For the connection of the ceramic matrix composite flame tube and the metal material connecting piece, a simple lap joint structure is adopted at present, and the designed metal connecting piece is in precise clearance fit with the connecting surface of the ceramic matrix composite flame tube at normal temperature (namely in the non-working state of the engine), so that good sealing can be formed, and the radial concentric positioning function of the flame tube can be ensured. However, at high temperature (i.e. in engine working state), the expansion of the ceramic matrix composite flame tube at the connecting surface is small due to the difference of expansion coefficients, while the expansion of the metal connecting piece is large, considering that the strength of the ceramic matrix composite is weak
The ceramic matrix composite flame tube is extremely easy to generate failure such as damage and the like; in addition, because the temperature resistance of the ceramic matrix composite is fully excavated in the design process, the performance of the engine is improved, and therefore, in the working state, the gas temperature at the outlet is higher, the metal connecting piece behind the connecting surface lacks air cooling, the ablation condition is extremely easy to generate, and the safe operation of the engine can be endangered due to the two failures.
Disclosure of Invention
The invention aims to provide a connecting structure of a ceramic matrix composite flame tube and a metal piece, which has an elastic structure, and can effectively reduce the thermal stress of the ceramic matrix composite flame tube and avoid damage; meanwhile, the cooling flow passage is arranged, so that the temperature of downstream metal parts can be effectively reduced, and ablation is avoided. In order to achieve the above purpose, the present invention provides the following technical solutions:
the invention provides a connecting structure of a ceramic matrix composite flame tube and a metal piece, wherein the connecting structure comprises the metal piece;
the metal piece comprises a metal runner mounting ring and an elastic supporting ring; wherein,
the metal runner mounting ring is connected with the elastic supporting ring through welding;
3-30 air entraining grooves are formed in the left side of the metal runner mounting ring;
and 3-40 stress release grooves are formed in the outer side of the elastic support ring.
Further, the connecting structure also comprises a ceramic matrix composite flame tube;
the ceramic matrix composite flame tube is connected with the elastic support ring of the metal piece through lap joint.
Further, the width a of the stress relief groove is 0.5-10 mm, and the depth b is 2-8 mm.
Further, the width c of the air entraining groove is 1-12 mm, and the depth d is 1-8 mm.
Further, the metal runner mounting ring is of an annular structure.
Further, the elastic support ring is an annular structure with an L-shaped cross section.
Further, the wall thickness of the cross section of the L-shaped annular structure is 0.3-1.5 mm.
Further, the bleed air grooves formed in the metal runner mounting ring and the stress release grooves formed in the elastic support ring form a cooling air runner together.
Further, the cooling air flow passage enables cooling air to flow into the high-temperature fuel air flow passage, and a cooling air film is formed near the wall surface of the metal flow passage mounting ring.
Further, the connecting structure further comprises a combustion chamber casing;
the combustion chamber casing is connected with the metal runner mounting ring of the metal piece through flange edges.
The invention has the technical effects and advantages that:
first, compared with other connection structures of ceramic matrix composite flame tubes and metal pieces, the metal connection of the invention
Second, the structure contains the L type elastic support ring that profile thickness is thinner to set up a plurality of stress relief groove, can effectively increase the elasticity of this structure, and then realize ceramic matrix composite flame tube and the less stress of metallic connection structure under high temperature operating condition, avoid ceramic matrix composite flame tube damage inefficacy.
And thirdly, the metal runner mounting ring is provided with a plurality of air entraining grooves which form a cooling air flow channel together with the stress release grooves, so that cooling air flow can be provided for metal parts at the downstream of the ceramic matrix composite flame tube, the cooling air flow can be realized by adjusting the flow area of the air entraining grooves and the stress release grooves, and finally, ablation failure of the downstream metal parts is avoided.
Additional features and advantages of the invention will be set forth in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention. The objectives and other advantages of the invention may be realized and attained by the structure particularly pointed out in the written description and claims hereof as well as the appended drawings.
Drawings
FIG. 1 is a schematic diagram of a conventional ceramic matrix composite and metal part connection structure;
FIG. 2 is a schematic diagram of a connection structure between a ceramic matrix composite flame tube and a metal piece according to the present invention;
FIG. 3 is a schematic view of a metal part according to the present invention;
FIG. 4 is a front view of the resilient support ring of the present invention;
FIG. 5 is a cross-sectional view of the resilient support ring of the present invention;
FIG. 6 is a front view of a metal runner mounting ring of the present invention;
FIG. 7 is a cross-sectional view of a metal runner mounting ring of the present invention;
in the figure, a 1-combustor casing; 2-ceramic matrix composite flame tube; 3-a rotation center line; 4-a metal runner mounting ring; 41-bleed air grooves; 5-an elastic support ring; 51-stress relief groove.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
In order to solve the defects in the prior art, the invention discloses a connecting structure of a ceramic matrix composite flame tube 2 and a metal piece, and fig. 2 is a schematic diagram of the connecting structure of the ceramic matrix composite flame tube 2 and the metal piece, as shown in fig. 2, wherein the connecting structure comprises the metal piece;
the metal piece comprises a metal runner mounting ring 4 and an elastic supporting ring 5; wherein,
the metal runner mounting ring 4 is connected with the elastic supporting ring 5 through welding;
3-30 air entraining grooves 41 are formed in the left side of the metal runner mounting ring 4;
the outer side of the elastic support ring 5 is provided with 3 to 40 stress relief grooves 51.
Preferably, the connection structure further comprises a ceramic matrix composite flame tube 2;
the ceramic matrix composite flame tube 2 is connected with the elastic support ring 5 of the metal piece in a lap joint mode.
Preferably, the stress relief groove 51 has a width a of 0.5 to 10mm and a depth b of 2 to 8mm.
Preferably, the width c of the bleed grooves 41 is 1-12 mm and the depth d is 1-8 mm.
Preferably, the metal runner mounting ring 4 has an annular structure.
Preferably, the elastic support ring 5 is an annular structure with an L-shaped section.
Preferably, the cross-sectional wall thickness of the L-shaped annular structure is 0.3-1.5 mm.
Preferably, the bleed air grooves 41 provided on the metal runner mounting ring 4 cooperate with the stress relief grooves 51 on the resilient support ring 5 to form a cooling air runner.
Preferably, the cooling air flow passage allows cooling air to flow into the high-temperature fuel air flow passage and forms a cooling film near the wall surface of the metal flow passage mounting ring 4.
Preferably, the connection structure further comprises a combustion chamber casing 1;
the combustion chamber casing 1 is connected with a metal runner mounting ring 4 of a metal piece through a flange edge;
referring to the working state of the aeroengine for illustration, the connecting structure of the ceramic matrix composite flame tube 2 and the metal piece is a closed structure formed by taking the rotation center line 3 in fig. 2 as a reference and rotating around the rotation center line 3 for one circle. When the aeroengine works, cooling air is contained in a cavity between the combustion chamber casing 1 and the ceramic matrix composite flame tube 2. The ceramic matrix composite flame tube 2 internally accommodates high-temperature fuel gas formed by combustion. The high-temperature fuel gas heats the ceramic matrix composite flame tube 2 and the metal runner mounting ring 4. At the same time, the ceramic matrix composite flame tube 2 will heat the elastic support ring 5 by means of heat conduction. Therefore, in the working state of the engine, the ceramic matrix composite flame tube 2, the metal runner mounting ring 4 and the elastic support ring 5 all have higher temperature and generate thermal expansion. Because the thermal expansion coefficient of the ceramic matrix composite flame tube 2 is only about 1/4 of that of the elastic supporting ring 5 of the metal piece, the radial expansion amount of the lap joint position of the ceramic matrix composite flame tube 2 is smaller than that of the elastic supporting ring 5, and the two parts tend to be extruded at the lap joint position. FIG. 3 is a schematic view of a metal part according to the present invention, and as shown in FIG. 3, the metal part includes a metal runner mounting ring 4 and an elastic support ring 5; wherein, the metal runner installing ring 4 is connected with the elastic supporting ring 5 by welding. Specifically, fig. 4 is a front view of the elastic support ring 5 of the present invention, fig. 5 is a cross-sectional view of the elastic support ring 5 of the present invention, and as shown in fig. 4 and 5, the elastic support ring 5 has an annular structure with an L-shaped cross section, the inner side is connected to the metal runner mounting ring 4, and the outer side is overlapped with the ceramic matrix composite flame tube 2. The L-shaped section wall thickness of the elastic support ring 5 is 0.3-1.5 mm. The outer side of the elastic supporting ring 5 is provided with 3 to 40 stresses
The stress relief groove 51 has a width a of 0.5 to 10mm and a depth b of 2 to 8mm. The stress relief groove 51 is arranged to allow a certain radial shrinkage deformation in the radial direction, so that the thermal stress generated by extrusion tendency is relieved, and the ceramic matrix composite flame tube 2 is ensured not to be damaged.
Specifically, fig. 6 is a front view of the metal runner mounting ring 4 of the present invention, fig. 7 is a cross-sectional view of the metal runner mounting ring 4, and as shown in fig. 6 and 7, the metal runner mounting ring 4 has an annular structure, the inner side is connected to the combustion chamber casing 1, and the outer side is connected to the ceramic matrix composite flame tube 2 to form a gas inner runner downstream of the flame tube outlet. 3 to 30 air entraining grooves 41 are arranged on the left side of the metal runner mounting ring 4, the width c of the air entraining grooves 41 is 1 to 12mm, and the depth d is 1 to 8mm. The bleed grooves 41 on the metal runner mount ring 4 together with the stress relief grooves 51 on the elastic support ring 5 form a runner for cooling air. The flow passage allows cooling air to flow into the high-temperature fuel gas flow passage, and a cooling air film is formed at the wall surface close to the metal flow passage mounting ring 4, so that the temperature of the part of the metal flow passage mounting ring 4 is reduced, and ablation is avoided. Meanwhile, when cooling air flows through the inner wall surface of the elastic support ring 5, part of heat of the elastic support ring 5 can be taken away through a convection heat exchange mode, the temperature of the elastic support ring 5 is reduced, the radial expansion amount of the elastic support ring is reduced, the thermal stress of the elastic support ring 5 and the ceramic matrix composite flame tube 2 can be relieved, and the ceramic matrix composite flame tube 2 is prevented from being damaged. The amount of cooling air flow can be adjusted as desired by changing the structural dimensions of the bleed air groove 41 and the stress relief groove 51.
The invention can finally improve the reliability of the connection structure of the ceramic matrix composite flame tube 2 and the downstream metal piece.
Finally, it should be noted that: the foregoing description is only illustrative of the preferred embodiments of the present invention, and although the present invention has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that modifications may be made to the embodiments described, or equivalents may be substituted for elements thereof, and any modifications, equivalents, improvements or changes may be made without departing from the spirit and principles of the present invention.
Claims (7)
1. The connecting structure of the ceramic matrix composite flame tube and the metal piece is characterized by comprising the metal piece;
the metal piece comprises a metal runner mounting ring (4) and an elastic supporting ring (5); wherein,
the metal runner mounting ring (4) is connected with the elastic supporting ring (5) through welding; the metal runner mounting ring (4) is of an annular structure, and the elastic supporting ring (5) is of an annular structure with an L-shaped section;
3-30 air entraining grooves (41) are formed in the left side of the metal runner mounting ring (4);
3-40 stress release grooves (51) are formed in the outer side of the elastic support ring (5);
the bleed air grooves (41) arranged on the metal runner mounting ring (4) and the stress relief grooves (51) on the elastic support ring (5) form a cooling air runner together.
2. A connection structure of a ceramic matrix composite flame tube and a metal piece according to claim 1, characterized in that the connection structure further comprises a ceramic matrix composite flame tube (2);
the ceramic matrix composite flame tube (2) is connected with the elastic supporting ring (5) of the metal piece in a lap joint mode.
3. The connection structure of a ceramic matrix composite flame tube and a metal piece according to claim 1, wherein the stress relief groove (51) has a width a of 0.5-10 mm and a depth b of 2-8 mm.
4. A connection of a ceramic matrix composite flame tube to a metal piece according to claim 1, characterized in that the width c of the bleed grooves (41) is 1-12 mm and the depth d is 1-8 mm.
5. The connection structure of the ceramic matrix composite flame tube and the metal piece according to claim 1, wherein the cross-section wall thickness of the L-shaped annular structure is 0.3-1.5 mm.
6. The connection structure of a ceramic matrix composite flame tube and a metal piece according to claim 1, wherein the cooling air flow passage enables cooling air to flow into a high-temperature fuel air flow passage and forms a cooling air film near the wall surface of the metal flow passage mounting ring (4).
7. The connection structure of a ceramic matrix composite flame tube and a metal piece according to claim 1, wherein the connection structure further comprises a combustion chamber casing (1);
the combustion chamber casing (1) is connected with a metal runner mounting ring (4) of the metal piece through flange edges.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211133069.2A CN115507392B (en) | 2022-09-16 | 2022-09-16 | Connection structure of ceramic matrix composite flame tube and metal piece |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211133069.2A CN115507392B (en) | 2022-09-16 | 2022-09-16 | Connection structure of ceramic matrix composite flame tube and metal piece |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN115507392A CN115507392A (en) | 2022-12-23 |
| CN115507392B true CN115507392B (en) | 2024-04-02 |
Family
ID=84503626
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211133069.2A Active CN115507392B (en) | 2022-09-16 | 2022-09-16 | Connection structure of ceramic matrix composite flame tube and metal piece |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115507392B (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1590850A (en) * | 2003-08-28 | 2005-03-09 | 诺沃皮尼奥内控股有限公司 | Fixing system of a flame pipe or liner |
| CN204438185U (en) * | 2014-12-19 | 2015-07-01 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | A kind of combustion chamber water conservancy diversion lining |
| CN104864416A (en) * | 2015-04-22 | 2015-08-26 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Connecting structure of combustion liner and transition section |
| CN106482156A (en) * | 2015-09-02 | 2017-03-08 | 通用电气公司 | Burner assembly for turbogenerator |
| CN107120687A (en) * | 2016-02-25 | 2017-09-01 | 通用电气公司 | burner assembly |
| CN113587147A (en) * | 2021-07-28 | 2021-11-02 | 中国航发湖南动力机械研究所 | Ceramic base flame tube positioning structure |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2825787B1 (en) * | 2001-06-06 | 2004-08-27 | Snecma Moteurs | FITTING OF CMC COMBUSTION CHAMBER OF TURBOMACHINE BY FLEXIBLE LINKS |
-
2022
- 2022-09-16 CN CN202211133069.2A patent/CN115507392B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1590850A (en) * | 2003-08-28 | 2005-03-09 | 诺沃皮尼奥内控股有限公司 | Fixing system of a flame pipe or liner |
| CN204438185U (en) * | 2014-12-19 | 2015-07-01 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | A kind of combustion chamber water conservancy diversion lining |
| CN104864416A (en) * | 2015-04-22 | 2015-08-26 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Connecting structure of combustion liner and transition section |
| CN106482156A (en) * | 2015-09-02 | 2017-03-08 | 通用电气公司 | Burner assembly for turbogenerator |
| CN107120687A (en) * | 2016-02-25 | 2017-09-01 | 通用电气公司 | burner assembly |
| CN113587147A (en) * | 2021-07-28 | 2021-11-02 | 中国航发湖南动力机械研究所 | Ceramic base flame tube positioning structure |
Also Published As
| Publication number | Publication date |
|---|---|
| CN115507392A (en) | 2022-12-23 |
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