Combustion chamber outer casing and aero-engine

Abstract

The utility model provides a combustion chamber outer casing and an aero-engine, and relates to the technical field of aero-engine structures. The outer casing of the combustion chamber comprises a casing body and a heat insulation blanket wrapping the outer side of the casing body. The heat insulation blanket comprises a heat insulation layer and a protection layer which are stacked, the heat insulation layer is fixedly attached to the outer side face of the casing body, and the protection layer is located on the side, away from the casing body, of the heat insulation layer. On one hand, the heat insulation blanket wraps the casing body, so that the difficulty of arranging a heat insulation structure on the complex casing body is reduced, on the other hand, the heat insulation blanket is composed of the heat insulation layer tightly attached to the outer side of the casing body and the protection layer covering the heat insulation layer, and the heat insulation layer is not prone to falling off. The heat insulation effect is greatly improved, heat transferred outwards by the outer casing through heat convection and heat radiation is weakened, the core cabin works within a certain temperature limiting range, and therefore the risk that accessories in the core cabin fail due to long-time work in a high-temperature environment is reduced.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft engine structures, in particular to an outer casing of a combustion chamber and an aircraft engine. Background Art

[0002] Due to the high mainstream temperature of the combustion chamber, the outer casing of the combustion chamber is a thin-walled part, and its maximum temperature can reach about 700°C. The use limit temperature of some sensors in the core cabin is 200°C. The heat transfer formula of thermal radiation is: Among them, Q is the radiation heat transfer; Cn is the radiation coefficient; T1, T2 are the temperatures of the two objects; F1 is the radiation surface area of ​​the radiator. When the temperature difference between the two is large, the radiation heat transfer increases exponentially, so there is a risk of overheating. The temperature determination principles of various accessories installed after the core cabin are as follows: Figure 1 As a result, accessories in the core cabin may suffer adverse effects such as loss of function or reduction in service life in a high temperature environment.

[0003] Therefore, in order to protect the accessories behind the core engine room and avoid adverse effects such as loss of function or reduction in service life in a high-temperature environment, a heat shield structure is often required. The application of heat shield structures in the field of aircraft engines is very common. By adding insulation materials or insulation structures between high-temperature components and low-temperature components, heat transfer can be effectively blocked, thereby protecting low-temperature components or structures, ensuring their normal functions, and extending service life. However, how to set a heat insulation structure on the outer casing of the combustion chamber to reduce the surface temperature of the outer casing, weaken high-temperature heat convection and thermal radiation effects, and ensure that the core engine room accessories work within a normal temperature range is a problem that needs to be solved at present. Utility Model Content

[0004] The purpose of the utility model is to provide an outer casing of a combustion chamber, which can effectively block heat transfer, weaken high-temperature heat convection and heat radiation effects, and ensure that core cabin accessories operate within a normal temperature range.

[0005] The utility model also aims to provide an aircraft engine that can effectively block heat transfer, weaken high-temperature heat convection and heat radiation effects, and ensure that core cabin accessories operate within a normal temperature range.

[0006] The embodiments of the present invention can be implemented in the following ways:

[0007] A combustion chamber outer casing, the combustion chamber outer casing comprising a casing body and a thermal insulation blanket covering the outer side of the casing body; the thermal insulation blanket comprises a stacked thermal insulation layer and a protective layer, the thermal insulation layer is fitted and fixed to the outer side surface of the casing body, and the protective layer is located on the side of the thermal insulation layer away from the casing body.

[0008] Optionally, a mounting seat is provided in the middle portion of the receiver body, the mounting seat is used to install accessories, and the mounting seat is arranged to protrude compared to the outer side surface; the outer side surface includes a front side wall surface located in front of the mounting seat and a rear side wall surface located behind the mounting seat; the thermal insulation blanket includes a front side thermal insulation blanket portion and a rear side thermal insulation blanket portion, the front side thermal insulation blanket portion is fixed on the front side wall surface, and the rear side thermal insulation blanket portion is fixed on the rear side wall surface.

[0009] Optionally, a front flange mounting edge is further provided at the front end of the receiver body, and the front thermal insulation blanket portion is located between the front flange mounting edge and the mounting seat; two ends of the front thermal insulation blanket portion are respectively spaced apart from the front flange mounting edge and the mounting seat.

[0010] Optionally, the thermal insulation layer includes a front thermal insulation layer, the protective layer includes a front protective layer, the front thermal insulation layer and the front protective layer are stacked to form the front thermal insulation blanket portion; the front thermal insulation portion includes a front main body portion and a front end portion which are connected to each other, the front end portion is located on a side of the front main body portion close to the front flange mounting edge, and the thickness of the front end portion is less than the thickness of the front main body portion; the front protective layer is attached to the side of the front main body portion away from the front wall surface.

[0011] Optionally, a rear flange mounting edge is further provided at the rear end of the receiver body, and the rear thermal insulation blanket portion is located between the rear flange mounting edge and the mounting seat; both ends of the rear thermal insulation blanket portion are spaced apart from the rear flange mounting edge and the mounting seat, respectively.

[0012] Optionally, the thermal insulation layer includes a rear thermal insulation layer, the protective layer includes a rear protective layer, the rear thermal insulation layer and the rear protective layer are stacked to form the rear thermal insulation blanket portion; the rear thermal insulation portion includes a rear main body portion and a rear end portion which are connected to each other, the rear end portion is located on a side of the rear main body portion close to the rear flange mounting edge, and the thickness of the rear end portion is less than the thickness of the rear main body portion; the rear protective layer is attached to the side of the rear main body portion away from the rear wall surface.

[0013] Optionally, the material of the thermal insulation layer is ceramic fiber material; and the thickness of the thermal insulation layer is greater than or equal to 9 mm.

[0014] Optionally, the material of the protective layer is GH625 alloy; the thickness of the protective layer is greater than or equal to 0.1 mm.

[0015] Optionally, the surface of the protective layer is embossed.

[0016] An aircraft engine combustion chamber comprises an accessory and an outer casing of the combustion chamber as described above, wherein the accessory is mounted on the outer casing of the combustion chamber.

[0017] The beneficial effects of the combustion chamber outer casing and the aircraft engine provided by the embodiments of the utility model include:

[0018] An embodiment of the utility model provides an outer casing of a combustion chamber, which includes a casing body and an insulation blanket coated on the outside of the casing body. The insulation blanket includes an insulation layer and a protective layer arranged in layers, the insulation layer is fitted and fixed to the outer side of the casing body, and the protective layer is located on the side of the insulation layer away from the casing body. By coating the insulation blanket outside the casing body, the difficulty of setting up an insulation structure on a complex casing body is reduced. On the other hand, the insulation blanket is composed of a two-layer structure of an insulation layer tightly attached to the outside of the casing body and a protective layer covering the insulation layer, which greatly improves the insulation effect and reduces the heat transferred to the outside by the outer casing through thermal convection and thermal radiation, so that the core cabin works within a certain temperature limit range, thereby reducing the risk of failure of accessories in the core cabin due to long-term operation in a high temperature environment, and greatly improving the safety of aircraft engine operation.

[0019] The embodiment of the utility model also provides an aircraft engine, which includes the above-mentioned combustion chamber outer casing. Since the aircraft engine includes the above-mentioned combustion chamber outer casing, it also has the beneficial effect of greatly improving the heat insulation effect, reducing the heat transferred to the outside by the outer casing through heat convection and heat radiation, so that the core cabin works within a certain temperature limit range, thereby reducing the risk of failure of accessories in the core cabin due to long-term operation in a high temperature environment, and greatly improving the safety of the aircraft engine operation. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] The above features and advantages of the present invention can be better understood after reading the detailed description of the embodiments of the present disclosure in conjunction with the following drawings. In the drawings, the components are not necessarily drawn to scale, and components with similar related properties or features may have the same or similar reference numerals.

[0021] Figure 1 The principle of determining the temperature of various accessories behind the core cabin in the prior art is shown;

[0022] Figure 2 A schematic cross-sectional structure diagram of a combustion chamber outer casing provided according to one aspect of the utility model is shown;

[0023] Figure 3 A schematic cross-sectional structure diagram of an outer casing of a combustion chamber provided according to one aspect of the utility model is shown.

[0024] Reference numerals:

[0025] 100-combustion chamber outer casing; 110-casing body; 111-mounting seat; 112-front side wall; 113-rear side wall; 114-front flange mounting edge; 115-rear flange mounting edge; 120-insulation blanket; 121-front side insulation blanket portion; 122-rear side insulation blanket portion; 123-insulation layer; 124-front side insulation layer; 1241-front side end portion; 1242-front side main body portion; 125-rear side insulation layer; 1251-rear side end portion; 1252-rear side main body portion; 126-protective layer; 127-front side protective layer; 128-rear side protective layer. DETAILED DESCRIPTION

[0026] The present invention is described in detail below in conjunction with the accompanying drawings and specific embodiments. Note that the aspects described below in conjunction with the accompanying drawings and specific embodiments are only exemplary and should not be construed as limiting the scope of protection of the present invention.

[0027] In the description of the present utility model, it should be noted that if the terms "upper", "lower", "inside", "outside", "vertical" and the like appear, the orientation or position relationship indicated is based on the orientation or position relationship shown in the accompanying drawings, or is the orientation or position relationship in which the utility model product is usually placed when used, rather than indicating or implying that the device or element referred to must have a specific orientation or be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present utility model.

[0028] At the same time, it should be noted that the terms "first", "second", etc. are only used for distinguishing descriptions and cannot be understood as indicating or implying relative importance.

[0029] In the description of the present invention, it is also necessary to explain that, unless otherwise clearly specified or limited, the terms "installation", "connection" and "connection" should be understood in a broad sense, for example, it can be a fixed connection, an integral connection, or a detachable connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, or the internal communication of two components, etc. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0030] Related terms (in Chinese and English) and their explanations:

[0031] Thermal Insulation: A blanket-like material with heat preservation and insulation functions. It is a general term for all "single material or composite material thermal insulation blanket (felt) products made with organic or inorganic metals or non-metals as the main formula raw materials, supplemented by specific chemical material formulas and processes according to specific use environments and performance requirements";

[0032] Heat Conduction: Heat transfer phenomenon when there is no macroscopic movement in the medium;

[0033] Heat Convection: Also known as convection heat transfer, it refers to the heat transfer process caused by the relative displacement of particles in the fluid. It is one of the three ways of heat transfer.

[0034] Thermal radiation (Clearance): One of the three ways of heat transfer, which refers to the phenomenon that an object radiates electromagnetic waves due to its temperature;

[0035] Core Compartment: It is composed of the core cover and core casing, including the low-pressure turbine casing, and is a compartment used to accommodate the engine's external pipes, cables, and onboard accessories.

[0036] Figure 2 FIG. 1 shows a cross-sectional structural diagram of a combustion chamber outer casing 100 provided in this embodiment. Figure 3 This is a cross-sectional structural diagram of the combustion chamber outer casing 100 provided in this embodiment. Figure 2 and Figure 3 This embodiment provides a combustion chamber outer casing 100 and also provides an aircraft engine (not shown).

[0037] The aircraft engine includes a combustion chamber outer casing 100 and accessories, which are mounted on the combustion chamber outer casing 100. Specifically, the type of accessories can be set according to needs, such as Figure 1 At least one of the various accessories shown.

[0038] The combustion chamber outer casing 100 includes a casing body 110 and a thermal insulation blanket 120 coated on the outer side of the casing body 110. The thermal insulation blanket 120 includes a stacked thermal insulation layer 123 and a protective layer 126. The thermal insulation layer 123 is fixedly attached to the outer side of the casing body 110, and the protective layer 126 is located on the side of the thermal insulation layer 123 away from the casing body 110. By coating the thermal insulation blanket 120 on the outside of the casing body 110, the difficulty of setting a thermal insulation structure on the complex casing body 110 is reduced. On the other hand, the thermal insulation blanket 120 is composed of a thermal insulation layer 123 tightly attached to the outer side of the casing body 110 and a protective layer 126 covering the thermal insulation layer 123. The thermal insulation effect is greatly improved, and the heat transferred to the outside of the outer casing through thermal convection and thermal radiation is reduced, so that the core cabin works within a certain temperature limit range, thereby reducing the risk of failure of accessories in the core cabin due to long-term operation in a high temperature environment, and greatly improving the safety of aircraft engine operation.

[0039] The combustion chamber outer casing 100 provided in this embodiment is further described below:

[0040] Please continue to refer to Figure 2 and Figure 3 In this embodiment, the combustion chamber casing is a substantially cylindrical structure, and the heat insulation blanket 120 is coated and attached to the outside of the casing body 110, thereby reducing the heat transferred to the outside through heat convection and heat radiation. Optionally, the heat insulation blanket 120 is configured to be composed of multiple sections uniformly distributed along the circumference of the casing body 110, for example, it can be configured to be a ring-shaped heat insulation blanket 120 formed by splicing three sections uniformly distributed along the circumference of the casing body 110.

[0041] The thermal insulation blanket 120 is a two-layer structure, which includes a laminated thermal insulation layer 123 and a protective layer 126. Optionally, the material of the thermal insulation layer 123 includes but is not limited to ceramic fiber material, which has a low thermal conductivity and can effectively insulate. Optionally, the thickness of the thermal insulation layer 123 is greater than or equal to 9 mm, that is, the thickness of the thermal insulation layer 123 includes but is not limited to 9 mm, 10 mm or 12 mm, etc.

[0042] Optionally, the protective layer 126 includes but is not limited to GH625 alloy (GH625 alloy is a solid solution strengthened nickel-based deformable high temperature alloy with molybdenum and niobium as main strengthening elements). GH625 alloy has good thermal conductivity, which can further dissipate heat on the one hand, and protect the thermal insulation layer 123 on the other hand. Optionally, the thickness of the protective layer 126 is greater than or equal to 0.1 mm, that is, the thickness of the protective layer 126 includes but is not limited to 0.1 mm, 0.5 mm or 1 mm, etc.

[0043] Furthermore, the surface of the protective layer 126 is embossed, thereby effectively increasing the heat exchange area and helping to improve the heat dissipation effect of the protective layer 126. Specifically, the surface of the protective layer 126 away from the heat insulation layer 123 is embossed, and the specific embossing pattern can be selected according to needs. Optionally, the embossing height is greater than or equal to 0.7 mm.

[0044] Please continue to refer to Figure 2 and Figure 3 In this embodiment, a mounting seat 111 is provided in the middle of the casing body 110, and the mounting seat 111 is used to mount accessories, and the mounting seat 111 is protruded from the outer side surface of the casing body 110. The outer side surface includes a front side wall surface 112 located in front of the mounting seat 111 and a rear side wall surface 113 located in the rear side of the mounting seat 111. The thermal insulation blanket 120 includes a front side thermal insulation blanket portion 121 and a rear side thermal insulation blanket portion 122, wherein the front side thermal insulation blanket portion 121 is fixed on the front side wall surface 112, and the rear side thermal insulation blanket portion 122 is fixed on the rear side wall surface 113.

[0045] Furthermore, the front insulation blanket portion 121 and the rear insulation blanket portion 122 are spaced apart from the mounting seat 111 , thereby ensuring that the front insulation blanket portion 121 and the rear insulation blanket portion 122 can be in close contact with the outer side surface of the casing body 110 .

[0046] Optionally, the front end of the casing body 110 is further provided with a front flange mounting edge 114, and the front side heat insulation blanket portion 121 is located between the front flange mounting edge 114 and the mounting seat 111. Specifically, the front flange mounting edge 114 is located at the end of one axial end of the casing body 110, and the front side wall surface 112 is the portion of the outer side surface located between the mounting seat 111 and the front flange mounting edge 114. Accordingly, the front side heat insulation blanket portion 121 fixedly attached to the front side wall surface 112 is located between the front flange mounting edge 114 and the mounting seat 111. Further, in order to ensure that the installation of the front side heat insulation blanket portion 121 will not affect the assembly of the bolts on the front flange mounting edge 114, the front side heat insulation blanket portion 121 is spaced apart from the front flange mounting edge 114.

[0047] Furthermore, the heat insulating layer 123 includes a front heat insulating layer 124, the protective layer 126 includes a front protective layer 127, and the front heat insulating layer 124 and the front protective layer 127 are stacked to form a front heat insulating blanket portion 121. The front heat insulating portion includes a front body portion 1242 and a front end portion 1241 connected to each other, the front end portion 1241 is located on a side of the front body portion 1242 close to the front flange mounting edge 114, and the thickness of the front end portion 1241 is less than the thickness of the front body portion 1242. The front protective layer 127 is attached to a side of the front body portion 1242 away from the front wall surface 112.

[0048] Specifically, the front insulation blanket portion 121 is also a two-layer structure formed by laminating an insulation layer 123 and a protective layer 126. The insulation layer 123 of the front insulation blanket portion 121 is the front insulation layer 124, and the protective layer 126 of the front insulation blanket portion 121 is the front protective layer 127. The thickness of the front insulation layer 124 near the front flange mounting edge 114 is relatively small, and the portion with relatively small thickness forms the front end portion 1241; the thickness of the front insulation layer 124 near the mounting seat 111 is relatively large, and the portion with relatively large thickness forms the front main body portion 1242. The thickness of the insulation layer 123 mentioned above can be regarded as the thickness of the front main body portion 1242. The front end 1241 is not covered with the protective layer 126. In other words, the front protective layer 127 is only attached to the front main body 1242. At this time, the front end 1241 of the front insulation blanket part 121 is a single-layer structure, and the front main body 1242 is a double-layer structure. Optionally, the thickness of the front end 1241 is halved compared to the thickness of the front main body 1242.

[0049] Optionally, the rear end of the casing body 110 is further provided with a rear flange mounting edge 115, and the rear side heat insulation blanket portion 122 is located between the rear flange mounting edge 115 and the mounting seat 111. Specifically, the rear flange mounting edge 115 is located at the end of the other axial end of the casing body 110, that is, the front flange mounting edge 114 and the rear flange mounting edge 115 are respectively located at the two ends of the axial direction of the casing body 110. The rear side wall surface 113 is the portion of the outer side surface located between the mounting seat 111 and the rear flange mounting edge 115. Accordingly, the rear side heat insulation blanket portion 122 fixedly attached to the rear side wall surface 113 is located between the rear flange mounting edge 115 and the mounting seat 111. Further, in order to ensure that the installation of the rear side heat insulation blanket portion 122 will not affect the assembly of the bolts on the rear flange mounting edge 115, the rear side heat insulation blanket portion 122 is spaced apart from the rear flange mounting edge 115.

[0050] Furthermore, the heat insulating layer 123 includes a rear heat insulating layer 125, and the protective layer 126 includes a rear protective layer 128. The rear heat insulating layer 125 and the rear protective layer 128 are stacked to form a rear heat insulating blanket portion 122. The rear heat insulating portion includes a rear main body portion 1252 and a rear end portion 1251 connected to each other. The rear end portion 1251 is located on a side of the rear main body portion 1252 close to the rear flange-shaped edge, and the thickness of the rear end portion 1251 is less than the thickness of the rear main body portion 1252. The rear protective layer 128 is attached to a side of the rear main body portion 1252 away from the rear wall surface 113.

[0051] Specifically, the rear insulation blanket portion 122 is also a two-layer structure formed by stacking an insulation layer 123 and a protective layer 126. The insulation layer 123 of the rear insulation blanket portion 122 is the rear insulation layer 125, and the protective layer 126 of the rear insulation blanket portion 122 is the rear protective layer 128. The thickness of the portion of the rear insulation layer 125 close to the rear flange mounting edge 115 is relatively small, and the portion with relatively small thickness forms the rear end portion 1251; the thickness of the portion of the rear insulation layer 125 close to the mounting seat 111 is relatively large, and the portion with relatively large thickness forms the rear main body portion 1252. The thickness of the insulation layer 123 mentioned above can be regarded as the thickness of the rear main body portion 1252. The rear end portion 1251 is not covered with the protective layer 126. In other words, the rear protective layer 128 is only attached to the rear main body portion 1252. At this time, the rear end portion 1251 of the rear insulation blanket portion 122 is a single-layer structure, and the rear main body portion 1252 is a double-layer structure. Optionally, the thickness of the rear end portion 1251 is halved compared to the thickness of the rear main body portion 1252.

[0052] The combustion chamber outer casing 100 and the aircraft engine provided by the embodiment of the utility model are provided by attaching and fixing the thermal insulation blanket 120 on the casing body 110 of the combustion chamber outer casing 100. The core material of the thermal insulation blanket 120 is an outer ceramic fiber material, and a layer of thin-walled metal material is added to the outer surface as a protective layer 126 to protect the inner ceramic thermal insulation layer 123, thereby greatly improving the safety of engine operation. The thermal insulation blanket 120 can effectively reduce the surface temperature of the outer casing, reduce the heat transferred to the outside by the outer casing through thermal convection and thermal radiation, so that the core cabin works within a certain temperature limit range, thereby reducing the risk of failure of accessories in the core cabin due to long-term operation in a high temperature environment.

[0053] The above is only a specific implementation of the present invention, but the protection scope of the present invention is not limited thereto. Any changes or substitutions that can be easily conceived by any technician familiar with the technology in this field within the technical scope disclosed by the present invention should be included in the protection scope of the present invention.

Claims

1. A combustion chamber outer casing, characterized in that: The combustion chamber outer casing includes a casing body and a thermal insulation blanket covering the outer side of the casing body; the thermal insulation blanket includes a stacked thermal insulation layer and a protective layer, the thermal insulation layer is bonded and fixed to the outer side surface of the casing body, and the protective layer is located on the side of the thermal insulation layer away from the casing body.

2. The combustion chamber outer casing according to claim 1, characterized in that: The middle part of the receiver body is provided with a mounting seat, which is used to install accessories, and the mounting seat is protruding compared to the outer side surface; the outer side surface includes a front wall surface located in front of the mounting seat and a rear wall surface located behind the mounting seat; the thermal insulation blanket includes a front thermal insulation blanket portion and a rear thermal insulation blanket portion, the front thermal insulation blanket portion is fixed on the front wall surface, and the rear thermal insulation blanket portion is fixed on the rear wall surface.

3. The combustion chamber outer casing according to claim 2, characterized in that: The front end of the casing body is also provided with a front flange mounting edge, and the front side heat insulation blanket portion is located between the front flange mounting edge and the mounting seat; the two ends of the front side heat insulation blanket portion are respectively spaced apart from the front flange mounting edge and the mounting seat.

4. The combustion chamber outer casing according to claim 3, characterized in that: The thermal insulation layer includes a front thermal insulation layer, and the protective layer includes a front protective layer, and the front thermal insulation layer and the front protective layer are stacked to form the front thermal insulation blanket portion; the front thermal insulation portion includes a front main body portion and a front end portion that are connected to each other, and the front end portion is located on a side of the front main body portion close to the front flange mounting edge, and the thickness of the front end portion is less than the thickness of the front main body portion; the front protective layer is attached to a side of the front main body portion away from the front wall surface.

5. The combustion chamber outer casing according to claim 2, characterized in that: The rear end of the receiver body is also provided with a rear flange mounting edge, and the rear side thermal insulation blanket portion is located between the rear flange mounting edge and the mounting seat; the two ends of the rear side thermal insulation blanket portion are respectively spaced apart from the rear flange mounting edge and the mounting seat.

6. The combustion chamber outer casing according to claim 5, characterized in that: The thermal insulation layer includes a rear thermal insulation layer, and the protective layer includes a rear protective layer, and the rear thermal insulation layer and the rear protective layer are stacked to form the rear thermal insulation blanket portion; the rear thermal insulation portion includes a rear main body portion and a rear end portion that are connected to each other, and the rear end portion is located on a side of the rear main body portion close to the rear flange mounting edge, and the thickness of the rear end portion is less than the thickness of the rear main body portion; the rear protective layer is attached to a side of the rear main body portion away from the rear wall surface.

7. The combustion chamber outer casing according to claim 1, characterized in that: The material of the heat insulation layer is ceramic fiber material; the thickness of the heat insulation layer is greater than or equal to 9 mm.

8. The combustion chamber outer casing according to claim 1, characterized in that: The material of the protective layer is GH625 alloy; the thickness of the protective layer is greater than or equal to 0.1 mm.

9. The combustion chamber outer casing according to claim 1, characterized in that: The surface of the protective layer is embossed.

10. An aircraft engine, characterized in that: The aircraft engine comprises an accessory and a combustion chamber outer casing according to any one of claims 1 to 9, wherein the accessory is mounted on the combustion chamber outer casing.

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