CN210289935U - Exhaust device for aircraft engine and combined machine of exhaust device and turbine - Google Patents
Exhaust device for aircraft engine and combined machine of exhaust device and turbine Download PDFInfo
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- CN210289935U CN210289935U CN201921352353.2U CN201921352353U CN210289935U CN 210289935 U CN210289935 U CN 210289935U CN 201921352353 U CN201921352353 U CN 201921352353U CN 210289935 U CN210289935 U CN 210289935U
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Abstract
An exhaust device for an aircraft engine comprises an annular outer casing, a hollow rectifying support plate and an annular inner casing, wherein the hollow rectifying support plate is uniformly supported in the diameter direction of the annular outer casing and the annular inner casing, and an airflow channel is formed by the inner surface of the outer casing, the outer surface of the inner casing and the molded surface of the hollow rectifying support plate; the structure of the annular outer casing is that the front end is a round table-shaped horn cylinder, the rear end is a cylindrical cylinder, and the annular inner casing is a cylindrical cylinder with the diameter smaller than that of the outer casing. The vertical section of the hollow rectifying support plate is streamline. The utility model overcomes the defects that the casting of the traditional process or the integral processing requires a special mould; the utility model discloses an electron beam welding supports the structure of extension board: the part has simple structure, easy processing, short development period and low cost, and the cost advantage is obvious in single-piece production.
Description
Technical Field
The utility model relates to an exhaust apparatus and preparation for the aeroengine especially relate to one kind and are applied to exhaust apparatus and turbine for high performance engine, belong to aircraft engine manufacturing technical field.
Background
With the further development of aircrafts, high requirements are put forward on the performance of an aircraft engine, the working temperature of an exhaust device and a turbine for the aircraft engine reaches above 1300 ℃, the passing influence on airflow is small, the prior art adopts a casting or integral processing method, and a special die is needed for casting; the integral processing needs integral castings, the processing period is long, and the cost is high.
In view of the present stringent requirements for aircraft development regarding satisfactory exhausts and turbines for engine combustors, the applicant has recognized that there is a need to produce exhausts and combined turbines for aircraft engines that have a long life in high temperature environments and that have high performance.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to overcome prior art's above-mentioned defect, provide a turbine of exhaust apparatus and combination for aeroengine, at operating temperature 1500 + 1600 ℃ within range, reach more than working life 10000s, satisfy the index requirement of high performance engine combustion chamber back end exhaust and turbine, alleviate the quality, provide technical support for improving engine specific impulse, extension aircraft flight life.
The above object of the present invention is achieved by the following technical solutions: an exhaust device and a turbine for an aircraft engine comprise an annular outer casing 1, a hollow rectifying support plate 5 and an annular inner casing 7, wherein the hollow rectifying support plate is uniformly supported in the diameter direction of the annular outer casing and the annular inner casing, and the inner surface of the outer casing and the outer surface of the inner casing and the molded surface of the hollow rectifying support plate form an airflow channel. The structure of the annular outer casing is that the front end is a round table-shaped horn cylinder, the rear end is a cylindrical cylinder, and the annular inner casing is a cylindrical cylinder with the diameter smaller than that of the outer casing.
Furthermore, the vertical section of the hollow rectifying support plate is streamline. Six hollow rectifying support plates are uniformly distributed on the ring.
The hollow rectifying support plate is welded between the inner ring surface of the annular outer casing and the outer ring surface of the annular inner casing, the exhaust casing inner casing is welded between the inner casing and the outer casing of the exhaust device, and the hollow rectifying support plate is arranged in the exhaust device.
The turbine using the exhaust device for an aircraft engine of the present application is located in front of the exhaust device on the air passage of the engine, even the aircraft engine itself.
Advantageous effect, the utility model provides an exhaust apparatus and turbine for aeroengine, the last hollow rectification extension board that has of exhaust apparatus is in the structure that the diameter direction of the outer cartridge receiver of loop type and the interior cartridge receiver of loop type evenly supported, enough intensity has and does not influence the stability of exhaust air current, little to the influence of passing through of exhaust air current, the turbine can be installed to the front end of the outer cartridge receiver of loop type, adopt electron beam welding can guarantee the performance of nai temperature, the internal surface of outer cartridge receiver and the surface of interior cartridge receiver form airflow channel with the profile of hollow rectification extension board, and the quality of whole structure is even with the distribution of transportation inertia. The defect that a special die is needed for casting in the traditional process of casting or integral processing is overcome; the whole processing cycle is long, and is with high costs, the utility model discloses a structure that electron beam welding supported the extension board: the part has simple structure, easy processing, short development period and low cost, and the cost advantage is obvious in single-piece production.
Drawings
Fig. 1 is a schematic view of the overall structure of the present invention.
Fig. 2 is a schematic view of the structure of the outer casing of the present invention.
Fig. 3 is a schematic structural view of the inner casing of the present invention.
Fig. 4 is a schematic diagram of the outer supporting plate structure of the present invention.
Detailed Description
As shown in the figure, the utility model discloses an exhaust apparatus for aeroengine, casing 7 constitutes in casing 1, hollow rectification extension board 5 and the loop type outside the loop type, and hollow rectification extension board 5 evenly supports in the diameter direction of annular casing at the outer casing inner tube of loop type and the outer surface of casing in the loop type, and hollow rectification extension board is six evenly distributed on the ring. The inner surface of the outer casing and the outer surface of the inner casing form an airflow channel with the molded surface of the hollow rectifying support plate. Take welding exhaust casing of hollow rectification extension board is welded structure: the parts have simple structure, easy processing, short development period and low cost, and the single-piece production is particularly obvious.
The structure of the annular outer casing is that the front end is a round platform-shaped horn barrel 2, the rear end is a cylindrical barrel 4, and the annular inner casing 7 is a cylindrical barrel with the diameter smaller than that of the outer casing. The front end of the cone-shaped horn 2 is provided with a flange 3 for connecting with a casing of a turbine. The front end of the ring-shaped inner casing is also provided with a flange 6 for connection to the rear end part of the turbine. The electron beam welding is a method for welding by using heat energy generated by bombarding a weldment placed in vacuum or non-vacuum by using accelerated and focused electron beams. The electron beam welding is widely applied to aviation preparation because of the advantages of no welding rod, difficult oxidation, good process repeatability and small thermal deformation.
The vertical cross section of the hollow rectifying support plate 5 is streamlined, as shown in fig. 2. The hollow rectifying support plate is welded between the inner ring surface of the annular outer casing and the outer ring surface of the annular inner casing, the exhaust casing inner casing is welded between the inner casing and the outer casing of the exhaust device, and the hollow rectifying support plate is arranged in the exhaust device.
Claims (4)
1. An exhaust device for an aircraft engine is characterized by comprising an annular outer casing, a hollow rectifying support plate and an annular inner casing, wherein the hollow rectifying support plate is uniformly supported in the diameter direction of the annular outer casing and the annular inner casing, and an airflow channel is formed by the inner surface of the outer casing, the outer surface of the inner casing and the molded surface of the hollow rectifying support plate; the structure of the annular outer casing is that the front end is a round table-shaped horn cylinder, the rear end is a cylindrical cylinder, and the annular inner casing is a cylindrical cylinder with the diameter smaller than that of the outer casing.
2. An aircraft engine exhaust device according to claim 1 wherein the vertical cross-section of the hollow rectifying support plate is streamlined.
3. An aircraft engine exhaust device according to claim 2 wherein the hollow rectifying support plates are evenly distributed in six on the ring.
4. A turbine in combination with an exhaust system for an aircraft engine according to any of claims 1 to 3, wherein the turbine is located in front of the exhaust system in the engine's air path.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921352353.2U CN210289935U (en) | 2019-08-20 | 2019-08-20 | Exhaust device for aircraft engine and combined machine of exhaust device and turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921352353.2U CN210289935U (en) | 2019-08-20 | 2019-08-20 | Exhaust device for aircraft engine and combined machine of exhaust device and turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN210289935U true CN210289935U (en) | 2020-04-10 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201921352353.2U Active CN210289935U (en) | 2019-08-20 | 2019-08-20 | Exhaust device for aircraft engine and combined machine of exhaust device and turbine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN210289935U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112345170A (en) * | 2020-10-22 | 2021-02-09 | 中国航发贵州黎阳航空动力有限公司 | Aeroengine supporting casing airtightness detection clamp and detection method |
| CN113982707A (en) * | 2021-11-04 | 2022-01-28 | 中国航发沈阳黎明航空发动机有限责任公司 | Aeroengine unloading cavity exhaust steering support plate |
-
2019
- 2019-08-20 CN CN201921352353.2U patent/CN210289935U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112345170A (en) * | 2020-10-22 | 2021-02-09 | 中国航发贵州黎阳航空动力有限公司 | Aeroengine supporting casing airtightness detection clamp and detection method |
| CN113982707A (en) * | 2021-11-04 | 2022-01-28 | 中国航发沈阳黎明航空发动机有限责任公司 | Aeroengine unloading cavity exhaust steering support plate |
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