CN113494362A - Ignition electric nozzle mounting assembly, combustion chamber and aircraft engine - Google Patents
Ignition electric nozzle mounting assembly, combustion chamber and aircraft engine Download PDFInfo
- Publication number
- CN113494362A CN113494362A CN202010277703.4A CN202010277703A CN113494362A CN 113494362 A CN113494362 A CN 113494362A CN 202010277703 A CN202010277703 A CN 202010277703A CN 113494362 A CN113494362 A CN 113494362A
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- Prior art keywords
- mounting
- base
- ignition
- section
- circular tube
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Classifications
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- 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
- F02C7/26—Starting; Ignition
- F02C7/264—Ignition
- F02C7/266—Electric
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- 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
- F23R3/007—Continuous combustion chambers using liquid or gaseous fuel constructed mainly of ceramic components
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- 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
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- 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
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Ceramic Engineering (AREA)
- Spark Plugs (AREA)
Abstract
The present disclosure relates to an ignition torch mounting assembly, a combustion chamber and an aircraft engine. Wherein, ignition nozzle installation component includes: the ignition electric nozzle mounting seat is used for mounting an ignition electric nozzle; and the base is made of ceramic matrix composite materials and used for installing the ignition nozzle mounting base on the outer wall of the flame tube. Through setting up the base of being made by ceramic matrix composite, ignition torch mount pad passes through the pedestal mounting on the outer wall of flame tube, has realized the fixed mounting of ignition torch mount pad on the flame tube of being made by ceramic matrix composite, guarantees the installation reliability.
Description
Technical Field
The utility model relates to an aeroengine technical field especially relates to an ignition electric nozzle installation component, combustion chamber and aeroengine.
Background
Ceramic matrix composites (ceramic matrix composites) have the characteristics of high temperature resistance, low density, low expansion coefficient, high specific strength, high specific modulus, oxidation resistance, ablation resistance, insensitivity to cracks, no catastrophic damage and the like, are increasingly and widely applied to preparation of hot-end structural components of new-generation aero-engines, and hot-end stator components become main application objects of CMC at the present stage due to simpler load conditions and lower load magnitude. The ceramic matrix composite material is adopted on the flame tube of the combustion chamber of the aircraft engine, so that the weight of parts in the combustion chamber can be reduced, the amount of cold air is reduced, and the performance and efficiency of the engine are improved.
An ignition electric nozzle is designed in the combustion chamber of the aero-engine and used for igniting the oil-gas mixture so as to enable the combustion chamber to start working. Generally, the ignition electric nozzle is fixed on the outer casing and needs to extend into the flame tube through the electric nozzle hole on the flame tube, and meanwhile, due to inconsistent flame combustion and thermal expansion, the position of the flame tube relative to the outer casing can change in work and is accompanied with vibration, so that the positions of the electric nozzle hole on the ignition electric nozzle and the flame tube need to be sealed, and gas is prevented from leaking to the outside of the flame tube when the positions of the ignition electric nozzle and the flame tube change. In the related technical scheme, the flame tube is made of high-temperature alloy, the electric nozzle mounting seat made of the high-temperature alloy is welded on the flame tube, and the sealing element is designed on the electric nozzle mounting seat and used for sealing a gap between the ignition electric nozzle and the electric nozzle hole. After the ceramic matrix composite is adopted to prepare the flame tube, the welding method cannot be used for fixing the electric nozzle mounting seat made of high-temperature alloy on the flame tube, and a brand new structural design is required for mounting the electric nozzle mounting seat.
Disclosure of Invention
The inventor finds that the problem that a flame tube made of a ceramic matrix composite material cannot be welded with an ignition nozzle mounting seat made of a metal material exists in the related art.
In view of this, the present disclosure provides an ignition nozzle mounting assembly, a combustion chamber and an aircraft engine, which can fixedly mount an ignition nozzle mounting base on a flame tube.
Some embodiments of the present disclosure provide an ignition tip mounting assembly, comprising:
the ignition electric nozzle mounting seat is used for mounting an ignition electric nozzle; and
and the base is made of ceramic matrix composite and used for mounting the ignition nozzle mounting base on the outer wall of the flame tube.
In some embodiments, the base comprises a base circular pipe section and a base flanging section, one side of the base flanging section is connected with one end of the base circular pipe section, the other side of the base flanging section is used for being fixedly connected with the outer wall of the flame tube, and the ignition electric nozzle mounting seat is installed on the base circular pipe section.
In some embodiments, the ignition electric nozzle mounting seat comprises a mounting seat circular tube section and a mounting seat flanging section, wherein one side of the mounting seat flanging section is provided with a mounting groove for mounting the sealing floating piece, the other side of the mounting seat flanging section is connected with one end of the mounting seat circular tube section, the mounting seat circular tube section is mounted in the base circular tube section, and the inside of the mounting seat circular tube section is used for inserting and mounting the ignition electric nozzle.
In some embodiments, there is a first predetermined gap between the outer wall of the mount tube section and the inner wall of the base tube section at room temperature.
In some embodiments, the installation base comprises a base circular pipe section, a plurality of installation bolts and a plurality of screw holes, wherein the pipe wall of the base circular pipe section is circumferentially provided with a plurality of bolt through holes, the pipe wall of the installation base circular pipe section is circumferentially provided with a plurality of screw holes, and the installation bolts penetrate through the bolt through holes one by one and are in threaded connection with the screw holes one by one.
In some embodiments, the axis of the bolt through bore passes through and is perpendicular to the axis of the base circular tube segment.
In some embodiments, the mounting bolts are provided with axial vents for introducing cooling air into the mounting cup circular tube sections.
In some embodiments, the plurality of bolt through holes are arranged at equal intervals in the circumferential direction of the pipe wall of the base circular pipe section.
In some embodiments, there is a second preset clearance between the bolt through hole and the screw portion of the mounting bolt at room temperature.
Some embodiments of the present disclosure provide a combustion chamber comprising an ignition torch, a flame tube, and the aforementioned ignition torch mounting assembly.
In some embodiments, the liner is made of a ceramic matrix composite and is integrally formed with the base or bonded by a ceramic matrix.
Some embodiments of the present disclosure provide an aircraft engine comprising the aforementioned combustion chamber.
Therefore, according to the embodiment of the disclosure, by arranging the base made of the ceramic matrix composite material, the ignition nozzle mounting base is mounted on the outer wall of the flame tube through the base, so that the fixed mounting of the ignition nozzle mounting base on the flame tube made of the ceramic matrix composite material is realized, and the mounting reliability is ensured.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments of the disclosure and together with the description, serve to explain the principles of the disclosure.
The present disclosure may be more clearly understood from the following detailed description, taken with reference to the accompanying drawings, in which:
FIG. 1 is a cross-sectional view of the overall construction of some embodiments of the ignition tip mounting assembly of the present disclosure;
FIG. 2 is a schematic overall structural view of some embodiments of the ignition torch mounting assembly of the present disclosure;
FIG. 3 is a cross-sectional exploded view of some embodiments of the ignition torch mounting assembly of the present disclosure;
fig. 4 is an exploded perspective view of some embodiments of the ignition torch mounting assembly of the present disclosure.
Description of the reference numerals
1. A base; 2. an ignition electric nozzle mounting base; 3. installing a bolt; 4. an ignition electric nozzle; 5. a flame tube; 11. a base circular tube section; 12. a base flanging section; 13. a bolt through hole; 21. a mounting seat circular pipe section; 22. a mount flanging section; 23. a threaded hole; 24. mounting grooves; 31. a screw section; 32. a nut portion; 33. and an axial vent hole.
Detailed Description
Various exemplary embodiments of the present disclosure will now be described in detail with reference to the accompanying drawings. The description of the exemplary embodiments is merely illustrative and is in no way intended to limit the disclosure, its application, or uses. The present disclosure may be embodied in many different forms and is not limited to the embodiments herein. These embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art. It should be noted that: the relative arrangement of parts and steps, the composition of materials, numerical expressions and numerical values set forth in these embodiments are to be construed as merely illustrative, and not as limitative, unless specifically stated otherwise.
The use of "first," "second," and similar terms in this disclosure is not intended to indicate any order, quantity, or importance, but rather are used to distinguish one element from another. The word "comprising" or "comprises", and the like, means that the element preceding the word covers the element listed after the word, and does not exclude the possibility that other elements are also covered. "upper", "lower", "left", "right", and the like are used merely to indicate relative positional relationships, and when the absolute position of the object being described is changed, the relative positional relationships may also be changed accordingly.
In the present disclosure, when a specific device is described as being located between a first device and a second device, there may or may not be intervening devices between the specific device and the first device or the second device. When a particular device is described as being coupled to other devices, the particular device may be directly coupled to the other devices without intervening devices or may be directly coupled to the other devices with intervening devices.
All terms used in the present disclosure have the same meaning as understood by one of ordinary skill in the art to which the present disclosure belongs, unless otherwise specifically defined. It will be further understood that terms, such as those defined in commonly used dictionaries, should be interpreted as having a meaning that is consistent with their meaning in the context of the relevant art and will not be interpreted in an idealized or overly formal sense unless expressly so defined herein.
Techniques, methods, and apparatus known to those of ordinary skill in the relevant art may not be discussed in detail, but are intended to be part of the specification where appropriate.
As shown in fig. 1-4, some embodiments of the present disclosure provide an ignition plug mounting assembly, including: base 1 and ignition nozzle mount pad 2, wherein ignition nozzle mount pad 2 is used for installing ignition nozzle 4, and base 1 is made by ceramic matrix composite, and it is used for installing ignition nozzle mount pad 2 on the outer wall of flame tube 5.
In this embodiment, through setting up base 1 made by ceramic matrix composite, ignition torch mount pad 2 is installed on the outer wall of flame tube 5 through base 1, has realized the fixed mounting of ignition torch mount pad on the flame tube made by ceramic matrix composite, guarantees the installation reliability.
As shown in fig. 3, in some embodiments, the base 1 includes a base circular pipe section 11 and a base flange section 12, one side of the base flange section 12 is connected to one end of the base circular pipe section 11, the inside of the connection region may or may not contain continuous fibers, the other side of the base flange section 12 is used for being fixedly connected to the outer wall of the flame tube 5, and the ignition torch mounting base 2 is mounted on the base circular pipe section 11. The arrangement of the base flanging section 12 ensures the connection reliability of the base 1 and the outer wall of the flame tube 5, and the arrangement of the base circular tube section 11 ensures the connection stability of the base 1 and the ignition nozzle mounting seat 2, so that the device has high implementability and reliability.
In some embodiments, as shown in fig. 3, the ignition nozzle mounting seat 2 includes a mounting seat circular tube section 21 and a mounting seat flanging section 22, one side of the mounting seat flanging section 22 is provided with a mounting groove 24 for mounting the sealing floating member, the other side is connected with one end of the mounting seat circular tube section 21, the mounting seat circular tube section 21 is mounted in the base circular tube section 11, and the inside of the mounting seat circular tube section 21 is used for inserting and mounting the ignition nozzle 4. The installation seat circular pipe section 21 is installed in the base circular pipe section 11, installation reliability is improved, and installation space is saved. In some embodiments, there is a first predetermined gap between the outer wall of the mount circle segment 21 and the inner wall of the base circle segment 11 at room temperature. The size of the gap value of the first preset gap is the difference of thermal expansion amounts along the radius direction between the base circular pipe section 11 and the mounting seat circular pipe section 21 at the maximum working temperature, and thus the gap is set to ensure that large thermal mismatch stress cannot be generated between the ignition electric nozzle mounting seat 2 and the base 1 during high-temperature working.
In other embodiments, the installation seat circular tube section is installed outside the base circular tube section, so that the installation reliability can be ensured, and the installation space can be saved.
As to how to connect the mounting seat circular pipe section 21 and the base circular pipe section 11, in some embodiments, as shown in fig. 1 to 4, the ignition electric nozzle mounting assembly further includes a plurality of mounting bolts 3, each mounting bolt 3 includes a screw portion 31 and a nut portion 32, the nut portion 32 is an inner hexagon nut or an outer hexagon nut, an external thread is provided outside the screw portion 31, a plurality of bolt through holes 13 are provided on the pipe wall of the base circular pipe section 11 along the circumferential direction, a plurality of threaded holes 23 are provided on the pipe wall of the mounting seat circular pipe section 21 along the circumferential direction, and the plurality of mounting bolts 3 are threaded through the plurality of bolt through holes 13 and the plurality of threaded holes 23 one to one. The installation seat circular pipe section 21 and the base circular pipe section 11 are connected through the installation bolts, so that the connection stability and reliability are guaranteed, and the realization is easy. The number of the mounting bolts 3 is 2, 3 or 4 as shown in fig. 4, or even more, and the number of the bolt through holes 13 and the threaded holes 23 is the same as the number of the mounting bolts 3.
As shown in fig. 3, in some embodiments, the axis of the bolt through hole 13 passes through and is perpendicular to the axis of the base circular pipe segment 11 to improve the connection stability. On the other hand, in some embodiments, a plurality of bolt through holes 13 are arranged at equal intervals in the circumferential direction of the pipe wall of the base circular pipe section 11, and the connection stability is also improved.
As shown in fig. 3, in some embodiments, the mounting bolt 3 is provided with an axial vent hole 33, and the axial vent hole 33 penetrates through the screw portion 31 and the nut portion 32, and is used for introducing cold air into the mounting seat circular tube section 21 to cool metal parts such as the ignition nozzle 4, the ignition nozzle mounting seat 2 and the sealing floating member.
In some embodiments, a second predetermined gap is formed between the bolt through hole 13 and the screw portion 31 of the mounting bolt 3 at room temperature, and the gap value of the second predetermined gap is the difference between the thermal expansion amounts of the screw portion 31 and the bolt through hole 13 along the radius direction at the maximum working temperature, so that the gap is set to ensure that the screw portion 31 does not generate large extrusion stress on the bolt through hole 13 due to thermal expansion during high-temperature working, and the bolt through hole 13 is prevented from being damaged and failing.
Some embodiments of the present disclosure provide a combustion chamber comprising an ignition torch 4, a flame tube 5, and the aforementioned ignition torch mounting assembly, thereby improving combustion reliability stability of the combustion chamber.
In some embodiments, the liner 5 is made of a ceramic matrix composite and is formed integrally with the base 1 or bonded thereto by a ceramic matrix. In other embodiments, holes are formed in the base flanging section 12 and the outer wall surface of the flame tube 5, ceramic rivets are driven into the holes for connection, and after the rivets are placed for connection, a ceramic substrate is prepared on the surfaces of the holes to cover the holes so as to prevent oxygen from oxidizing and corroding fibers around the holes and at the rivets in the working process.
Some embodiments of the present disclosure provide an aircraft engine comprising the aforementioned combustion chamber, thereby improving the operational reliability and stability of the aircraft engine.
Thus, various embodiments of the present disclosure have been described in detail. Some details that are well known in the art have not been described in order to avoid obscuring the concepts of the present disclosure. It will be fully apparent to those skilled in the art from the foregoing description how to practice the presently disclosed embodiments.
Although some specific embodiments of the present disclosure have been described in detail by way of example, it should be understood by those skilled in the art that the foregoing examples are for purposes of illustration only and are not intended to limit the scope of the present disclosure. It will be understood by those skilled in the art that various changes may be made in the above embodiments or equivalents may be substituted for elements thereof without departing from the scope and spirit of the present disclosure. The scope of the present disclosure is defined by the appended claims.
Claims (12)
1. An ignition plug mounting assembly, comprising:
the ignition electric nozzle mounting base (2) is used for mounting an ignition electric nozzle (4); and
the base (1) is made of ceramic matrix composite materials and used for installing the ignition nozzle mounting seat (2) on the outer wall of the flame tube (5).
2. The ignition nozzle mounting assembly according to claim 1, wherein the base (1) comprises a base circular tube section (11) and a base flanging section (12), one side of the base flanging section (12) is connected with one end of the base circular tube section (11), the other side of the base flanging section is fixedly connected with the outer wall of the flame tube (5), and the ignition nozzle mounting seat (2) is mounted on the base circular tube section (11).
3. The ignition nozzle mounting assembly according to claim 2, wherein the ignition nozzle mounting seat (2) comprises a mounting seat circular tube section (21) and a mounting seat flanging section (22), one side of the mounting seat flanging section (22) is provided with a mounting groove (24) for mounting a sealing floating piece, the other side of the mounting seat flanging section is connected with one end of the mounting seat circular tube section (21), the mounting seat circular tube section (21) is mounted in the base circular tube section (11), and the inside of the mounting seat circular tube section (21) is used for inserting and mounting the ignition nozzle (4).
4. The ignition nozzle mounting assembly according to claim 3, wherein a first predetermined gap is provided between the outer wall of the mounting seat circular tube section (21) and the inner wall of the base circular tube section (11) at room temperature.
5. The ignition nozzle mounting assembly according to claim 3, further comprising a plurality of mounting bolts (3), wherein a plurality of bolt through holes (13) are circumferentially formed in the tube wall of the base circular tube section (11), a plurality of threaded holes (23) are circumferentially formed in the tube wall of the mounting base circular tube section (21), and the plurality of mounting bolts (3) are threaded through the plurality of bolt through holes (13) one by one and are in threaded connection with the plurality of threaded holes (23) one by one.
6. The ignition nozzle mounting assembly according to claim 5, wherein the axis of the bolt through hole (13) passes through and is perpendicular to the axis of the base circular tube section (11).
7. Ignition nozzle mounting assembly according to claim 5, characterized in that the mounting bolt (3) is provided with an axial vent hole (33) for introducing cold air into the mounting seat circular tube section (21).
8. The ignition nozzle mounting assembly according to claim 5, wherein a plurality of the bolt through holes (13) are arranged at equal intervals in a circumferential direction of a pipe wall of the base circular pipe section (11).
9. The ignition nozzle mounting assembly according to claim 5, wherein a second preset clearance is provided between the bolt through hole (13) and the screw portion (31) of the mounting bolt (3) at room temperature.
10. A combustion chamber comprising an ignition torch (4), a flame tube (5) and an ignition torch mounting assembly as claimed in any one of claims 1 to 9.
11. A combustion chamber as claimed in claim 10, characterized in that said flame tube (5) is made of ceramic matrix composite and is of integral structure with said base (1) or is bonded by means of a ceramic matrix.
12. An aircraft engine, characterized in that it comprises a combustion chamber according to claim 10 or 11.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010277703.4A CN113494362B (en) | 2020-04-08 | 2020-04-08 | Ignition electric nozzle mounting assembly, combustion chamber and aircraft engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010277703.4A CN113494362B (en) | 2020-04-08 | 2020-04-08 | Ignition electric nozzle mounting assembly, combustion chamber and aircraft engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113494362A true CN113494362A (en) | 2021-10-12 |
| CN113494362B CN113494362B (en) | 2022-12-16 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010277703.4A Active CN113494362B (en) | 2020-04-08 | 2020-04-08 | Ignition electric nozzle mounting assembly, combustion chamber and aircraft engine |
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| Country | Link |
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| CN (1) | CN113494362B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116105177A (en) * | 2023-03-10 | 2023-05-12 | 中国航发湖南动力机械研究所 | Ceramic-based flame tube |
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| GB1476414A (en) * | 1974-04-05 | 1977-06-16 | Gen Motors Corp | Combustion apparatus for a gas turbine engine |
| US6351949B1 (en) * | 1999-09-03 | 2002-03-05 | Allison Advanced Development Company | Interchangeable combustor chute |
| CN1573051A (en) * | 2003-06-20 | 2005-02-02 | Snecma发动机公司 | Plug sealing device that is not welded to the chamber wall |
| US20090235635A1 (en) * | 2008-03-21 | 2009-09-24 | Siemens Power Generation, Inc. | Igniter Assembly for a Gas Turbine |
| CN103486619A (en) * | 2012-06-13 | 2014-01-01 | 中国航空工业集团公司沈阳发动机设计研究所 | Flame tube fixing structure |
| CN105258159A (en) * | 2014-07-14 | 2016-01-20 | 联合工艺公司 | Additive manufactured surface finnish |
| CN108534178A (en) * | 2017-03-03 | 2018-09-14 | 通用电气公司 | Seal assembly for the component for penetrating CMC liner |
| CN209053698U (en) * | 2018-09-26 | 2019-07-02 | 中国航发商用航空发动机有限责任公司 | Ignition electric nozzle component, combustion chamber and the gas turbine of combustion chamber |
-
2020
- 2020-04-08 CN CN202010277703.4A patent/CN113494362B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1476414A (en) * | 1974-04-05 | 1977-06-16 | Gen Motors Corp | Combustion apparatus for a gas turbine engine |
| US6351949B1 (en) * | 1999-09-03 | 2002-03-05 | Allison Advanced Development Company | Interchangeable combustor chute |
| CN1573051A (en) * | 2003-06-20 | 2005-02-02 | Snecma发动机公司 | Plug sealing device that is not welded to the chamber wall |
| US20090235635A1 (en) * | 2008-03-21 | 2009-09-24 | Siemens Power Generation, Inc. | Igniter Assembly for a Gas Turbine |
| CN103486619A (en) * | 2012-06-13 | 2014-01-01 | 中国航空工业集团公司沈阳发动机设计研究所 | Flame tube fixing structure |
| CN105258159A (en) * | 2014-07-14 | 2016-01-20 | 联合工艺公司 | Additive manufactured surface finnish |
| CN108534178A (en) * | 2017-03-03 | 2018-09-14 | 通用电气公司 | Seal assembly for the component for penetrating CMC liner |
| CN209053698U (en) * | 2018-09-26 | 2019-07-02 | 中国航发商用航空发动机有限责任公司 | Ignition electric nozzle component, combustion chamber and the gas turbine of combustion chamber |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116105177A (en) * | 2023-03-10 | 2023-05-12 | 中国航发湖南动力机械研究所 | Ceramic-based flame tube |
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| CN113494362B (en) | 2022-12-16 |
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