CN114483311A - Compact type double-medium air inlet structure - Google Patents
Compact type double-medium air inlet structure Download PDFInfo
- Publication number
- CN114483311A CN114483311A CN202111662179.3A CN202111662179A CN114483311A CN 114483311 A CN114483311 A CN 114483311A CN 202111662179 A CN202111662179 A CN 202111662179A CN 114483311 A CN114483311 A CN 114483311A
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- China
- Prior art keywords
- air inlet
- annular cavity
- guide vanes
- external air
- hollow
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- 230000009977 dual effect Effects 0.000 claims 4
- 238000010168 coupling process Methods 0.000 description 2
- 238000005859 coupling reaction Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000006872 improvement Effects 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
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Classifications
-
- 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
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
Abstract
The invention discloses a compact type double-medium air inlet structure which comprises an external air inlet annular cavity, a hollow guide vane, an internal annular cavity and a turbine guide vane, wherein the external air inlet annular cavity is provided with a plurality of air inlet holes; the guide vanes are arranged between the external air inlet annular cavity and the internal annular cavity, are hollow and are respectively communicated with the external air inlet annular cavity and the internal annular cavity; an air inlet is arranged on the external air inlet annular cavity; a turbine guide vane is arranged in the inner annular cavity; the high-temperature air flows through the guide vanes and is discharged from the tail part; the low-temperature airflow is discharged after being guided to the interior of the structure from the outside through the air inlet, the external air inlet annular cavity, the hollow guide vanes and the internal annular cavity. The invention can meet the functional requirements of double-medium air intake and bearing.
Description
Technical Field
The invention relates to the technical field of engine air inlet structures, in particular to a compact double-medium air inlet structure.
Background
In the field of hypersonic air-breathing combined engines, the method of widening the working envelope of a turbine engine by using more efficient thermodynamic cycle is the most effective means adopted in the field of combined engines at present. In the efficient thermodynamic cycle process, the traditional air inlet structure cannot meet the structural requirements of multiple media and compactness in the multi-coupling cycle due to the complex structure and highly-compact overall structural design brought by the multi-coupling cycle.
Disclosure of Invention
In view of this, the invention provides a compact dual-medium air inlet structure, which can meet the requirements of dual-medium air inlet and force bearing functions.
The technical scheme adopted by the invention is as follows:
a compact double-medium air inlet structure comprises an external air inlet annular cavity, a hollow guide vane, an internal annular cavity and a turbine guide vane;
the guide vanes are arranged between the external air inlet annular cavity and the internal annular cavity, are hollow and are respectively communicated with the external air inlet annular cavity and the internal annular cavity; an air inlet is arranged on the external air inlet annular cavity; a turbine guide vane is arranged in the inner annular cavity;
the high-temperature air flows through the guide vanes and is discharged from the tail part; the low-temperature airflow is discharged after being guided to the interior of the structure from the outside through the air inlet, the external air inlet annular cavity, the hollow guide vanes and the internal annular cavity.
Furthermore, the hollow guide vane is twisted at a fixed height and a set angle from the vane root to the vane top; the direction of twist is determined by the direction of incoming flow.
Further, the fixed height is 20% of the leaf height.
Further, the outer profile of the outer air inlet ring cavity and the outer profile of the inner ring cavity are Vickers curves.
Furthermore, the minimum flow areas of the air inlet, the external air inlet annular cavity, the hollow guide vanes and the internal annular cavity are set according to the requirements of the engine on the pressure and the flow of the low-temperature air.
Furthermore, the throat area of the turbine guide vane is set according to the requirements of the engine on low-temperature air pressure and flow.
Has the advantages that:
the high-temperature air flow is discharged from the tail part through the guide vanes; the low-temperature airflow is discharged after being drained from the outside to the inside of the structure through the air inlet, the external air inlet annular cavity, the hollow guide vanes and the internal annular cavity, so that double-medium simultaneous working is realized, the two-medium simultaneous working is integrated on one structure, and the structure is compact; and moreover, the outer air inlet annular cavity and the inner annular cavity are supported by hollow guide vanes with proper quantity, so that the bearing capacity of the air inlet annular cavity is ensured.
Drawings
Fig. 1 is a schematic view of the overall structure of the present invention.
Fig. 2 is a cross-sectional view of fig. 1.
Wherein, 1-external air inlet ring cavity, 2-hollow guide vanes, 3-internal ring cavity, 4-turbine guide vanes and 5-air inlet.
Detailed Description
The invention is described in detail below by way of example with reference to the accompanying drawings.
The invention provides a compact double-medium air inlet structure, which meets the structural requirements of double-medium air inlet and compactness, can bear two functions of air inlet and force bearing, and comprises an external air inlet annular cavity 1, a hollow guide vane 2, an internal annular cavity 3 and a turbine guide vane 4, as shown in figure 1.
The hollow guide vane 2 is arranged between the external air inlet annular cavity 1 and the internal annular cavity 3, is hollow and is respectively communicated with the external air inlet annular cavity 1 and the internal annular cavity 3; an air inlet 5 is arranged on the external air inlet annular cavity 1; and a turbine guide vane 4 is arranged in the inner annular cavity 3.
As shown in fig. 2, the high temperature air flow channel is composed of the lower profile of the external air inlet ring cavity 1, the upper profile of the internal ring cavity 3 and the shape of the hollow guide vane 2, and the high temperature air flow is discharged from the tail part through the guide vane to provide thrust; the low-temperature airflow is discharged after being drained from the outside to the inside of the structure through the air inlet 5, the external air inlet annular cavity 1, the hollow guide vanes 2 and the internal annular cavity 3, and the low-temperature turbine is driven to work.
The hollow guide vane 2 is twisted at a fixed height and a set angle from the vane root to the vane top; the direction of twist is determined by the direction of incoming flow. In this example, the fixed height is 20% of the leaf height, and the leaf is twisted 15 ° in the counterclockwise direction.
The outer molded surface of the external air inlet annular cavity 1 and the outer molded surface of the internal annular cavity 3 are classical shrinkage curve Vickers curves, and are generated by a calculation program through adjusting parameters in a formula.
The minimum flow areas of the air inlet 5, the external air inlet annular cavity 1, the hollow guide vanes 2 and the internal annular cavity 3 are set according to the requirements of the engine on the pressure and the flow of low-temperature air.
The turbine guide vane 4 is a traditional turbine guide vane, and the throat area of the turbine guide vane is set according to the requirements of the engine on low-temperature air pressure and flow.
In summary, the above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (6)
1. A compact double-medium air inlet structure is characterized by comprising an external air inlet annular cavity, a hollow guide vane, an internal annular cavity and a turbine guide vane;
the guide vanes are arranged between the external air inlet annular cavity and the internal annular cavity, are hollow and are respectively communicated with the external air inlet annular cavity and the internal annular cavity; an air inlet is arranged on the external air inlet annular cavity; a turbine guide vane is arranged in the inner annular cavity;
the high-temperature air flows through the guide vanes and is discharged from the tail part; the low-temperature airflow is discharged after being guided to the interior of the structure from the outside through the air inlet, the external air inlet annular cavity, the hollow guide vanes and the internal annular cavity.
2. The compact dual media air intake structure of claim 1, wherein the hollow guide vanes are twisted at a set angle of fixed height from the blade root to the blade tip; the direction of twist is determined by the direction of incoming flow.
3. The compact dual media intake structure of claim 2, wherein the fixed height is 20% of the lobe height.
4. The compact dual media air intake structure of any one of claims 1-3, wherein the outer profiles of the outer and inner intake annuli are Vickers curves.
5. The compact dual-media air intake structure of claim 4, wherein the minimum flow areas of the air inlet, the outer air intake annulus, the hollow guide vanes and the inner annulus are set according to the requirements of the engine on low-temperature air pressure and flow.
6. The compact dual media air intake structure of claim 5, wherein the throat area of the turbine guide vanes is set according to the requirements of the engine on low temperature gas pressure and flow.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111662179.3A CN114483311A (en) | 2021-12-31 | 2021-12-31 | Compact type double-medium air inlet structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111662179.3A CN114483311A (en) | 2021-12-31 | 2021-12-31 | Compact type double-medium air inlet structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114483311A true CN114483311A (en) | 2022-05-13 |
Family
ID=81508351
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111662179.3A Pending CN114483311A (en) | 2021-12-31 | 2021-12-31 | Compact type double-medium air inlet structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114483311A (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB700564A (en) * | 1951-04-18 | 1953-12-02 | Bristol Aeroplane Co Ltd | Improvements in or relating to turbo-jet engines |
| JPS5316108A (en) * | 1976-07-29 | 1978-02-14 | Gen Electric | Fluiddcooled element |
| CA2193165A1 (en) * | 1996-01-04 | 1997-07-05 | Isabelle Marie-Agnes Noiret | Cooled turbine vane |
| CN1243910A (en) * | 1998-07-31 | 2000-02-09 | 东芝株式会社 | High effective blade structure of turbine |
| US20050089393A1 (en) * | 2003-10-22 | 2005-04-28 | Zatorski Darek T. | Split flow turbine nozzle |
| CN110566285A (en) * | 2019-08-26 | 2019-12-13 | 中国人民解放军总参谋部第六十研究所 | Compact centripetal turbine guider |
-
2021
- 2021-12-31 CN CN202111662179.3A patent/CN114483311A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB700564A (en) * | 1951-04-18 | 1953-12-02 | Bristol Aeroplane Co Ltd | Improvements in or relating to turbo-jet engines |
| JPS5316108A (en) * | 1976-07-29 | 1978-02-14 | Gen Electric | Fluiddcooled element |
| CA2193165A1 (en) * | 1996-01-04 | 1997-07-05 | Isabelle Marie-Agnes Noiret | Cooled turbine vane |
| CN1243910A (en) * | 1998-07-31 | 2000-02-09 | 东芝株式会社 | High effective blade structure of turbine |
| US20050089393A1 (en) * | 2003-10-22 | 2005-04-28 | Zatorski Darek T. | Split flow turbine nozzle |
| CN110566285A (en) * | 2019-08-26 | 2019-12-13 | 中国人民解放军总参谋部第六十研究所 | Compact centripetal turbine guider |
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