CN119879232B - Gas turbine engine, combustion chamber and its manifold assembly - Google Patents
Gas turbine engine, combustion chamber and its manifold assemblyInfo
- Publication number
- CN119879232B CN119879232B CN202311395254.3A CN202311395254A CN119879232B CN 119879232 B CN119879232 B CN 119879232B CN 202311395254 A CN202311395254 A CN 202311395254A CN 119879232 B CN119879232 B CN 119879232B
- Authority
- CN
- China
- Prior art keywords
- manifold assembly
- combustion chamber
- sealing ring
- ring
- cooling air
- 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.)
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Links
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
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/26—Controlling the air flow
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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
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
- F23R3/045—Air inlet arrangements using pipes
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Gasket Seals (AREA)
Abstract
本发明的目的在于提供一种燃气涡轮发动机、燃烧室及其歧管组件，歧管组件包括连接口、收口部、密封圈、挡部以及弹性垫圈。在所述收口部与所述连接口之间形成肩部，密封圈设置于所述肩部，挡部设置于所述连接口的出口处内侧，弹性垫圈设置于所述挡部与所述密封圈之间。其中，所述密封圈沿所述连接口的径向可弹性变形，所述弹性垫圈在外力作用下可弹性变形，以允许所述密封圈沿所述连接口的轴向具有一定的位移量，通过本歧管组件能够保证燃烧室内冷却空气主动控制系统的密封性。
The present invention aims to provide a gas turbine engine, a combustion chamber, and a manifold assembly thereof. The manifold assembly includes a connector, a constriction portion, a sealing ring, a stop portion, and an elastic washer. A shoulder is formed between the constriction portion and the connector, the sealing ring is disposed on the shoulder, the stop portion is disposed inside the outlet of the connector, and the elastic washer is disposed between the stop portion and the sealing ring. The sealing ring is elastically deformable radially along the connector, and the elastic washer is elastically deformable under external force, allowing the sealing ring to have a certain amount of displacement axially along the connector. This manifold assembly ensures the sealing performance of the active cooling air control system within the combustion chamber.
Description
Technical Field
The invention relates to the technical field of gas turbine engines, in particular to a gas turbine engine, a combustion chamber and a manifold assembly thereof.
Background
At present, the fuel consumption rate of the aero-engine, especially the large bypass ratio civil aero-engine, is an important index of competition in the future international market. The working principle based on the aero-engine is mainly that after the high-pressure gas compressed by the high-pressure compressor is fully mixed with aviation kerosene flowing into a combustion chamber from a fuel oil adapter, the mixture is ignited by an ignition nozzle to be burnt vigorously and form high-temperature and high-pressure fuel gas, so that the gas is expanded and acted through turbine blades, and then the compressor is driven to work through a connecting shaft, so that the whole aero-engine is operated. In the process, the combustion chamber and the hot end part of the high-pressure turbine bear high-temperature and high-pressure fuel gas, and great challenges are brought to materials and cooling, so that in the overall structural design, in order to meet each working condition of the normal operation of an engine, the design needs to be carried out according to the worst working condition, and particularly the cooling design for the hot end part is particularly important, namely, in the high-temperature take-off state, the cooling air quantity for a movable blade body of the high-pressure turbine needs to meet the cooling design requirement. However, in a state of small thermal load of turbine blades such as cruising, no cold air corresponding to the high-temperature take-off cold air amount is needed, and therefore, an adjustment means, namely, a cooling air active control system is needed.
The cooling air active control system can effectively adjust the cooling air quantity of the hot end part under each working state, reduces the oil consumption of the engine, and because the device is an adjusting device, the external connection is directly connected into the hot end component, so that the hot end component is required to have good sealing performance, and how to ensure the sealing performance of the cooling air active control system is a problem to be solved at present.
Disclosure of Invention
The invention aims to provide a manifold assembly, which can ensure the tightness of an active control system of cooling air in a combustion chamber.
To achieve the foregoing object, a manifold assembly for a combustion chamber, comprising:
the cooling air active control system is connected with the combustion chamber through the connecting port;
a receiving portion, an inner diameter of the manifold assembly being tapered inwardly at the receiving portion to form a shoulder between the receiving portion and the connection port;
the sealing ring is arranged on the shoulder part, and the inner diameter of the sealing ring is smaller than the inner diameter of the receiving part;
a blocking part arranged at the inner side of the outlet of the connecting port, and
The elastic gasket is arranged between the blocking part and the sealing ring;
The sealing ring can elastically deform along the radial direction of the connecting port, and the elastic gasket can elastically deform under the action of external force so as to allow the sealing ring to have a certain displacement along the axial direction of the connecting port.
In one or more embodiments, an annular gasket is further disposed on both sides of the elastic gasket along an axial direction of the connection port.
In one or more embodiments, the elastic washer is in the shape of a bellows.
In one or more embodiments, a clamping groove is arranged on the inner side of the outlet of the connecting port, a clamping ring is arranged in the clamping groove, and the clamping ring forms the blocking part.
In one or more embodiments, the collar has an opening at which the outer diameter of the collar can be varied by applying a force.
In one or more embodiments, the seal ring is hollow, with an opening radially outward, which allows the seal ring to elastically deform under external forces such that the inner diameter of the seal ring is altered.
In another aspect, there is also provided in accordance with some embodiments of the present application a combustion chamber including a cooling air active control conditioning system, a combustion chamber outer casing, and a manifold assembly as previously described;
The cooling air active control and regulation system stretches into the combustion chamber outer casing from the outside and then stretches into the manifold assembly, and the sealing ring seals the joint of the cooling air active control and regulation system and the manifold assembly.
In one or more embodiments, the inner circumference of the seal ring is in line contact seal with the outer tube wall of the cooling air active control adjustment system, and the seal ring is elastically supported by the elastic gasket so that the end surface of the seal ring is in line contact seal with the shoulder.
In one or more embodiments, the inner diameter of the seal ring at the smallest of the inner ring is 1mm to 2mm smaller than the outer diameter of the outer tube of the air active control adjustment system.
In yet another aspect, according to some embodiments of the present application, there is also provided a gas turbine engine comprising a combustion chamber as previously described.
The invention has the beneficial effects that:
The manifold assembly is provided with an axial floating structure, two layers of annular gaskets are fixed in the manifold assembly through the clamping ring, an elastic gasket with an elastic structure is placed between the two annular gaskets, the structural size of the elastic gasket is controlled, the deformation of the elastic gasket between the two layers of annular gaskets is realized, after the air active control adjusting system penetrates into a pipeline through the position, the axial deformation of the engine under different working states can be adapted due to the axial movement provided by the elastic gasket, and damage caused by clamping stagnation of the cooling air control adjusting mechanism and the pipeline connection is avoided. The manifold assembly has the advantages of simple structure, convenient disassembly and assembly, and quick and convenient detection and maintenance, and can be replaced in time only through the common gasket, the clamping ring, the elastic gasket and the lip seal ring structure.
The foregoing description is only an overview of the present application, and is intended to be implemented in accordance with the teachings of the present application in order that the same may be more clearly understood and to make the same and other objects, features and advantages of the present application more readily apparent.
Drawings
Various other advantages and benefits will become apparent to those of ordinary skill in the art upon reading the following detailed description of the preferred embodiments. The drawings are only for purposes of illustrating the preferred embodiments and are not to be construed as limiting the application. Also, like reference numerals are used to designate like parts throughout the accompanying drawings. In the drawings:
FIG. 1 illustrates a schematic diagram of one embodiment of a combustion chamber;
FIG. 2 illustrates a schematic view in semi-section of some embodiments of the present manifold assembly;
FIG. 3 shows an enlarged partial schematic view of a connection port according to the present manifold assembly;
FIG. 4 illustrates a schematic perspective view of some embodiments of a collar;
Fig. 5 illustrates a perspective view of some embodiments of a seal ring according to the present disclosure.
Detailed Description
Embodiments of the technical scheme of the present application will be described in detail below with reference to the accompanying drawings. The following examples are only for more clearly illustrating the technical aspects of the present application, and thus are merely examples, and are not intended to limit the scope of the present application.
Unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application belongs, the terms used herein are for the purpose of describing particular embodiments only and are not intended to be limiting of the application, and the terms "comprising" and "having" and any variations thereof in the description of the application and the claims and the above description of the drawings are intended to cover non-exclusive inclusions.
The cooling air active control system (Modulated Tubine Cooling, abbreviated as MTC) is characterized in that the cooling air quantity of the high-pressure turbine is actively regulated according to different working states of the engine, when the high-pressure turbine is high in thermal load (such as take-off), enough cooling air is provided for the high-pressure turbine through the MTC, and when the high-pressure turbine is low in thermal load (such as cruising), the supply of the cooling air is properly reduced, so that the fuel consumption rate of the engine is reduced.
In order to achieve an effective sealing of the active control system for cooling air in the combustion chamber, according to some embodiments of the application, a combustion chamber is provided, as in fig. 1, which shows a schematic view according to an embodiment of the present combustion chamber, it being understood that the illustration shown in fig. 1 is merely matters, in order to show the structural connection between the main components in the combustion chamber, in fact the combustion chamber may have more structural details. The combustion chamber includes a cooling air active control and conditioning system 91, a combustion chamber housing 92, and a manifold assembly 100, specifically, in the components shown in the figures, the combustion chamber further includes a pre-diffuser 93, a flame tube 95, a pre-swirl nozzle 96, and other bolts. The cooling air actively controls the adjusting device 91 to directly penetrate into the combustion chamber outer casing 92 from the outside, then the whole device penetrates into the manifold structure 100, sealing is realized through the sealing structure of the manifold structure 100, meanwhile, the manifold structure 100 is directly fixed on the rear flange of the front diffuser 93 through bolts, and then a pipeline extends into the pre-rotation nozzle 96 through the inner ring cavity channel of the flame tube 95 and the inner casing, so that the air entraining function can be realized.
On the other hand, there is also provided a manifold assembly 100 according to some embodiments of the present application, wherein the manifold assembly 100 may be applied to the combustion chamber described in the foregoing embodiments, fig. 2 shows a semi-sectional schematic view of some embodiments of the manifold assembly, the manifold assembly 100 includes a connection port 1, a closing-in portion 2, a sealing ring 3, a blocking portion 4, and an elastic gasket 5, fig. 3 shows a partially enlarged schematic view of the connection port of the manifold assembly, the cooling air active control system 91 is connected to the combustion chamber through the connection port 1 of the manifold assembly 100, an inner diameter of the manifold assembly 100 is contracted in the closing-in portion 2 to form a shoulder 20 between the closing-in portion 2 and the connection port 1, the sealing ring 3 is disposed at the shoulder 20, and an inner diameter of the sealing ring 3 is smaller than an inner diameter of the closing-in portion 2. The baffle part 4 is arranged on the inner side of the outlet of the connecting port 1, and the elastic gasket 5 is arranged between the baffle part 4 and the sealing ring 3.
The sealing ring 3 can elastically deform along the radial direction a of the connection port 1, and the elastic gasket 5 can elastically deform under the action of external force, so as to allow the sealing ring 3 to have a certain displacement along the axial direction b of the connection port 1.
In the assembled state, the cooling air active control and adjustment system 91 extends into the combustion chamber housing 92 from the outside and then into the manifold assembly 100, and the seal ring 3 seals the joint between the cooling air active control and adjustment system 91 and the manifold assembly 100. The cooling air is directly supplied to the pre-rotation nozzle through the pipeline of the cooling air active control adjusting system 91 so as to supply high vortex cooling, in the process, the outer wall surface of the pipeline of the cooling air active control adjusting system 91 is different from the manifold assembly 100, the integral temperature field is different due to different fixing positions, meanwhile, due to direct contact, the thermal deformation incompatibility and leakage risk are caused, and the sealing ring 3 is configured to be elastically deformable along the radial direction a of the connecting port 1 and has a certain displacement space along the axial direction b of the connecting port 1 through the design of the patent, so that the axial floating quantity caused by the deformation incompatibility under different working states is adapted, the sealing of the connecting part is realized, the air tightness of the cooling air active control device can be ensured, and the influence caused by insufficient air quantity supply due to air leakage in the working process is avoided.
In the description of embodiments of the present application, the technical terms "first," "second," and the like are used merely to distinguish between different objects and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated, a particular order or a primary or secondary relationship. In the description of the embodiments of the present application, the meaning of "plurality" is two or more unless explicitly defined otherwise.
Reference herein to "an embodiment" means that a particular feature, structure, or characteristic described in connection with the embodiment may be included in at least one embodiment of the application. The appearances of such phrases in various places in the specification are not necessarily all referring to the same embodiment, nor are separate or alternative embodiments mutually exclusive of other embodiments. Those of skill in the art will explicitly and implicitly appreciate that the embodiments described herein may be combined with other embodiments.
In some embodiments of the manifold assembly, the annular gaskets 6 are further arranged on two sides of the elastic gasket 5 along the axial direction b of the connecting port 1, so that the elastic gasket 5 can apply force through the annular gaskets 6 on two sides, the stability of fixing the elastic gasket 5 is ensured, and the phenomena such as dislocation and the like are not easy to occur.
In some embodiments of the present manifold assembly, the elastomeric gasket 5 is corrugated annular. Specifically, the elastic washer 5 has a geometric center, and a minimum distance from the geometric center to the outer edge of the elastic washer 5 is the outer diameter of the elastic washer 5, and a reference circle is formed with the geometric center as a center and the outer diameter of the elastic washer 5 as a radius. The elastic washer 5 has at least one convex section which is convex relative to the plane of the reference circle and at least one concave section which is concave relative to the plane of the reference circle, the convex section and the concave section form the elastic washer 5 in a corrugated ring shape, and the distance between the convex section and the concave section relative to the plane of the reference circle defines the elastic deformation amount of the elastic washer 5. The elastic washer 5 with the configuration is easy to assemble and fix, and the displacement of the sealing ring 3 along the axial direction b of the connecting port 1 can be determined by adjusting the elastic deformation of the elastic washer 5 by adjusting the distance between the convex section and the concave section relative to the plane of the reference circle.
In some embodiments of the present manifold assembly, a clamping groove 10 is arranged on the inner side of the outlet of the connection port 1, a clamping ring is arranged in the clamping groove, and the clamping ring forms a blocking part 4. By means of the arrangement, the clamping ring can be assembled to form a part for limiting at the outlet of the connecting port 1, and the clamping ring can be replaced after being worn, so that the service life of the manifold assembly is prolonged. In other embodiments than the one shown in the figures, the stop 4 can also be a collar projecting towards the inside of the outlet of the connection opening 1.
Fig. 4 shows a schematic perspective view of some embodiments of the present collar, where the collar 4 has an opening 40, and where the outer diameter of the collar 4 can be changed by applying a force at the opening 40, thereby facilitating the fitting of the collar 4 in the card slot 10.
Fig. 5 shows a schematic perspective view of some embodiments of the present seal ring, wherein the seal ring 3 is hollow and has a seal ring upper end 30, a seal ring lower end 31 and a seal ring inner edge 32, and an opening 33 is provided at an outer edge of a seal ring radially outside between the seal ring upper end 30 and the seal ring lower end 31, and when the seal ring upper end 30 and the seal ring lower end 31 are forced, a size of the opening 33 can be changed, so that the seal ring 3 is elastically deformed to allow an inner diameter of the seal ring defined at the seal ring inner edge 32 to be changed.
In some embodiments of the present combustion chamber, in the assembled state, the inner circumference of the sealing ring 3 is in line contact and seal with the outer pipe wall of the cooling air active control and regulation system 91, and the sealing ring 3 is elastically supported by the elastic gasket 5, so that the end surface of the sealing ring 3, that is, the end surface of the lower end 31 of the sealing ring is in line contact and seal with the shoulder 20, and the reliability of the sealing effect is ensured.
In some embodiments of the combustion chamber, the inner diameter of the smallest part of the inner ring of the sealing ring 3 is smaller than the outer diameter of the outer tube of the air active control adjusting system 91 by 1 mm to 2 mm, so that when the air entraining tube of the air active control adjusting system 91 passes through the sealing ring 3, the structure of the sealing ring 3 can be extruded, the inner side wall surface is stressed outwards, meanwhile, as the sealing ring 3 is assembled on the lower sides of the double-layer annular gasket 6 and the elastic gasket 5, the elastic force of the elastic gasket 5 between the double-layer annular gasket 6 is acted, the radial stress of the elastic gasket is ensured, the radial displacement of the elastic gasket is limited, the end face of the upper end 30 of the sealing ring and the lower end face of the double-layer annular gasket 6 are subjected to linear sealing, the inner edge 32 of the sealing ring and the outer tube wall of the air active control adjusting system 91 are tightly attached to the shoulder 20 under the action of the force, the linear sealing is realized, and under the normal working state of the engine, the sealing structure can ensure the air tightness of the cooling air active control device, and the influence caused by insufficient air supply in the working process is avoided.
In yet another aspect, according to some embodiments of the present application, there is also provided a gas turbine engine comprising a combustion chamber as previously described.
The manifold assembly is provided with an axial floating structure, two layers of annular gaskets 6 are fixed in the manifold assembly through the clamping ring 4, an elastic gasket 5 with an elastic structure is placed between the two annular gaskets 6, wherein the structural size of the elastic gasket 5 is controlled, the deformation of the elastic gasket 5 between the two layers of annular gaskets 6 is realized, and the air active control and regulation system 91 penetrates into a pipeline through the position, and the axial deformation provided by the elastic gasket 5 can be adapted to the axial deformation of an engine under different working states due to the axial movement provided by the elastic gasket 5, so that the damage caused by the clamping stagnation of the cooling air control and regulation mechanism and the pipeline connection is avoided. The manifold assembly has the advantages of simple structure, convenient disassembly and assembly, and quick and convenient detection and maintenance, and can be replaced in time only through the common gasket, the clamping ring, the elastic gasket and the lip seal ring structure.
In the description of the embodiments of the present application, unless explicitly specified and limited otherwise, the terms "mounted," "connected," "fixed" and the like are to be construed broadly and include, for example, fixed connection, detachable connection, or integral therewith, mechanical connection, electrical connection, direct connection, indirect connection via an intermediary, communication between two elements, or interaction between two elements. The specific meaning of the above terms in the embodiments of the present application will be understood by those of ordinary skill in the art according to specific circumstances.
It is to be understood that references herein to "along" a direction means that there is at least a component in that direction, preferably within 10 ° of that direction, more preferably within 5 °.
It should be noted that the above embodiments are only used to illustrate the technical solution of the present application, but not to limit the technical solution of the present application, and although the detailed description of the present application is given with reference to the above embodiments, it should be understood by those skilled in the art that the technical solution described in the above embodiments may be modified or some or all technical features may be equivalently replaced, and these modifications or substitutions do not make the essence of the corresponding technical solution deviate from the scope of the technical solution of the embodiments of the present application, and all the modifications or substitutions are included in the scope of the claims and the specification of the present application. In particular, the technical features mentioned in the respective embodiments may be combined in any manner as long as there is no structural conflict. The present application is not limited to the specific embodiments disclosed herein, but encompasses all technical solutions falling within the scope of the claims.
Claims (8)
1. A manifold assembly for a combustion chamber, comprising:
the cooling air active control system is connected with the combustion chamber through the connecting port;
a receiving portion, an inner diameter of the manifold assembly being tapered inwardly at the receiving portion to form a shoulder between the receiving portion and the connection port;
the sealing ring is arranged on the shoulder part, and the inner diameter of the sealing ring is smaller than the inner diameter of the receiving part;
a blocking part arranged at the inner side of the outlet of the connecting port, and
The elastic gasket is arranged between the blocking part and the sealing ring;
The sealing ring can elastically deform along the radial direction of the connecting port, and the elastic gasket can elastically deform under the action of external force so as to allow the sealing ring to have a certain displacement along the axial direction of the connecting port;
Along the axial direction of the connecting port, annular gaskets are arranged on two sides of the elastic gasket;
The inner side of the outlet of the connecting port is provided with a clamping groove, a clamping ring is arranged in the clamping groove, and the clamping ring forms the blocking part.
2. The manifold assembly of claim 1, wherein the elastomeric gasket is corrugated annular.
3. The manifold assembly of claim 1, wherein the collar has an opening, the outer diameter of the collar being variable by applying a force at the opening.
4. The manifold assembly of claim 1, wherein the seal ring is hollow and has an opening radially outward, the opening allowing the seal ring to elastically deform under an external force such that an inner diameter of the seal ring is changed.
5. A combustion chamber comprising a cooling air active control conditioning system, a combustion chamber outer casing, and a manifold assembly according to any one of claims 1 to 4;
The cooling air active control and regulation system stretches into the combustion chamber outer casing from the outside and then stretches into the manifold assembly, and the sealing ring seals the joint of the cooling air active control and regulation system and the manifold assembly.
6. The combustion chamber of claim 5 wherein the inner periphery of said seal ring is in line contact seal with the outer tube wall of said cooling air active control conditioning system, said seal ring being resiliently supported by said resilient gasket such that the end face of said seal ring is in line contact seal with said shoulder.
7. The combustion chamber of claim 6, wherein the inner diameter of the seal ring at the smallest of the inner ring is 1 mm to 2mm smaller than the outer diameter of the outer tube of the air active control adjustment system.
8. A gas turbine engine comprising a combustion chamber as claimed in any one of claims 5 to 7.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311395254.3A CN119879232B (en) | 2023-10-25 | 2023-10-25 | Gas turbine engine, combustion chamber and its manifold assembly |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311395254.3A CN119879232B (en) | 2023-10-25 | 2023-10-25 | Gas turbine engine, combustion chamber and its manifold assembly |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN119879232A CN119879232A (en) | 2025-04-25 |
| CN119879232B true CN119879232B (en) | 2025-11-25 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311395254.3A Active CN119879232B (en) | 2023-10-25 | 2023-10-25 | Gas turbine engine, combustion chamber and its manifold assembly |
Country Status (1)
| Country | Link |
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| CN (1) | CN119879232B (en) |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1193451A2 (en) * | 2000-10-02 | 2002-04-03 | Rolls-Royce Deutschland Ltd & Co KG | Combustion chamber head of a gas turbine |
| CA2625330A1 (en) * | 2007-04-19 | 2008-10-19 | Pratt & Whitney Canada Corp. | Combustor liner with improved heat shield retention |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4191011A (en) * | 1977-12-21 | 1980-03-04 | General Motors Corporation | Mount assembly for porous transition panel at annular combustor outlet |
| US7647779B2 (en) * | 2005-04-27 | 2010-01-19 | United Technologies Corporation | Compliant metal support for ceramic combustor liner in a gas turbine engine |
| US7966820B2 (en) * | 2007-08-15 | 2011-06-28 | General Electric Company | Method and apparatus for combusting fuel within a gas turbine engine |
| US8276391B2 (en) * | 2010-04-19 | 2012-10-02 | General Electric Company | Combustor liner cooling at transition duct interface and related method |
-
2023
- 2023-10-25 CN CN202311395254.3A patent/CN119879232B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1193451A2 (en) * | 2000-10-02 | 2002-04-03 | Rolls-Royce Deutschland Ltd & Co KG | Combustion chamber head of a gas turbine |
| CA2625330A1 (en) * | 2007-04-19 | 2008-10-19 | Pratt & Whitney Canada Corp. | Combustor liner with improved heat shield retention |
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| Publication number | Publication date |
|---|---|
| CN119879232A (en) | 2025-04-25 |
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