CN110886627A - Integrated casing for combined engine - Google Patents
Integrated casing for combined engine Download PDFInfo
- Publication number
- CN110886627A CN110886627A CN201911047707.7A CN201911047707A CN110886627A CN 110886627 A CN110886627 A CN 110886627A CN 201911047707 A CN201911047707 A CN 201911047707A CN 110886627 A CN110886627 A CN 110886627A
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- CN
- China
- Prior art keywords
- helium
- casing
- gas
- outlet
- inlet
- 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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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/30—Exhaust heads, chambers, or the like
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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
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses an integrated casing for a combined engine, and belongs to the technical field of structural design of combined engines. The casing is of a hollow annular cavity structure, gas collecting cavities are respectively arranged at two ends of the annular cavity structure and are communicated with the outside through a through hole structure on the outer circumferential surface of the annular cavity structure, the two gas collecting cavities are respectively a helium outlet and a gas inlet, the through hole structure corresponding to the helium outlet is a helium inlet, the through hole structure corresponding to the gas inlet is a gas outlet, the gas inlet is connected with an external combustion chamber outlet casing, and the helium inlet is connected with a high-temperature heat exchanger pipeline. The invention can meet the requirements of compact structure and low flow resistance of the combined engine by coupling the helium gas inlet flow pipe with the gas casing.
Description
Technical Field
The invention belongs to the technical field of combined engine structure design, and particularly relates to an engine case structure adopting two working media.
Background
In the field of hypersonic air suction type combined engines, a third medium fluid (generally helium) is used for cooling high-temperature incoming air to reduce the air flow temperature in front of an air compressor, the scheme for widening the working speed range of a turbine engine is an important development direction of the conventional hypersonic engine, a helium turbine is usually used for replacing a gas turbine to drive the air compressor in the scheme of the hypersonic engine, the conventional gas exhaust casing and a helium gas inlet casing are loose in structure, the size of a part is large, the length of an air compressor-helium turbine shafting is increased, the reliable work of the shafting is not facilitated, the axial size of the engine is greatly increased, and the requirement for the high-compactness structural design of the engine cannot be met.
Disclosure of Invention
In view of this, the present invention provides an integrated casing for a combined engine, which can meet the requirements of compact structure and low flow resistance of the combined engine.
The integrated casing for the combined engine is characterized in that the casing is of a hollow annular cavity structure, gas collecting cavities are respectively arranged at two ends of the annular cavity structure and are communicated with the outside through a through hole structure on the outer circumferential surface of the annular cavity structure, the two gas collecting cavities are respectively a helium outlet and a fuel gas inlet, the through hole structure corresponding to the helium outlet is a helium inlet, and the through hole structure corresponding to the fuel gas inlet is a fuel gas outlet.
Further, the gas collecting cavity is of an annular structure.
Furthermore, a bearing seat is arranged at the center of one end of the casing.
Furthermore, the helium inlets and the fuel gas outlets are sequentially and alternately distributed on the outer circumferential surface of the annular cavity structure.
Furthermore, the outer profile of the casing adopts a Wisconsin type line.
Furthermore, the fuel gas inlet is connected with an external combustion chamber outlet casing in a non-standard flange bolt connection mode, and the helium gas inlet is connected with an external high-temperature heat exchanger pipeline in a non-standard flange bolt connection mode.
Has the advantages that:
1. the integrated casing structure structurally couples the helium gas inlet flow pipe with the gas casing, realizes the mutual fusion of the helium gas pipeline and the gas casing, can greatly shorten the axial dimension of the casing, fully utilizes the limited space in the engine and meets the design requirement of the engine on compactness.
2. According to the invention, the bearing seat is arranged at the central position of one end of the casing, so that the corresponding mounting structure can be arranged in the casing, the axial mounting space is not occupied, and the structure is more compact.
3. The internal and external molded surfaces of the integrated casing adopt the Wisconsissian molded line, so that the increased flow resistance can be controlled in the minimum range, and the requirement of low flow resistance of the whole engine is met.
Drawings
FIG. 1 is a schematic structural view of an integrated casing for a combined engine according to the present invention;
FIG. 2 is a schematic view of a gas flow path of the integrated casing for the combined engine according to the present invention;
FIG. 3 is a schematic helium flow path of the integrated case for a combined engine of the present invention.
Wherein, the gas bearing comprises a helium outlet 1, a helium inlet 2, a gas outlet 3, a gas inlet 4 and a bearing seat 5.
Detailed Description
The invention is described in detail below by way of example with reference to the accompanying drawings.
As shown in the attached drawing 1, the invention provides an integrated casing for a combined engine, the whole appearance of the casing is a hollow annular cavity structure, two ends of the annular cavity structure are respectively provided with an annular gas collecting cavity, the two gas collecting cavities are respectively a helium gas outlet 1 and a gas inlet 4, the helium gas outlet 1 is communicated with a through hole structure on the outer circumferential surface of the annular cavity structure, namely a helium gas inlet 2, and the gas inlet 4 is communicated with a through hole structure on the outer circumferential surface of the annular cavity structure, namely a gas outlet 3; and a bearing seat 5 is arranged at the center of one side of the helium outlet 1 of the casing.
The gas inlet 4 is connected with the combustion chamber outlet casing in a non-standard flange bolt connection mode, high-temperature gas flows into the gas inlet 4 of the integrated casing from an annular cavity of the combustion chamber outlet, and a gas flow path is shown in figure 2, flows out through the four gas outlets 3, enters the high-temperature heat exchanger and exchanges heat with a helium working medium.
The helium inlet 2 is connected with a pipeline of the high-temperature heat exchanger in a non-standard flange bolt connection mode, helium which exchanges heat with gas in the high-temperature heat exchanger enters the integrated casing through the four helium inlets, flows out of the helium outlet 1 through a helium flow path shown in figure 3, and blows a helium turbine to do work in a rotating mode.
In summary, the above description is only a preferred embodiment of the present invention, and is not intended to limit the protection 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. The integrated casing for the combined engine is characterized in that the casing is of a hollow annular cavity structure, gas collecting cavities are arranged at two ends of the annular cavity structure respectively and are communicated with the outside through a through hole structure on the outer circumferential surface of the annular cavity structure, the two gas collecting cavities are respectively a helium outlet and a fuel gas inlet, the through hole structure corresponding to the helium outlet is a helium inlet, and the through hole structure corresponding to the fuel gas inlet is a fuel gas outlet.
2. An integral barrel for a compound engine as set forth in claim 1, wherein said plenum is of annular configuration.
3. An integral case for a combined engine as set forth in claim 1 or 2, wherein a bearing seat is provided at a central position of one end of said case.
4. The integral case for a combined engine as set forth in claim 3, wherein said helium gas inlet and said gas outlet are alternately arranged in sequence on the outer circumferential surface of said annular chamber structure.
5. The integral case for a compound engine as set forth in claim 4, wherein said outer profile of said case is of the Wisconsin type.
6. The integrated casing for the combined engine as set forth in claim 5, wherein said gas inlet is bolted to an external combustion chamber outlet casing by non-standard flange bolts, and said helium inlet is bolted to an external high temperature heat exchanger pipe by non-standard flange bolts.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911047707.7A CN110886627B (en) | 2019-10-30 | 2019-10-30 | Integrated casing for combined engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911047707.7A CN110886627B (en) | 2019-10-30 | 2019-10-30 | Integrated casing for combined engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110886627A true CN110886627A (en) | 2020-03-17 |
| CN110886627B CN110886627B (en) | 2022-07-29 |
Family
ID=69746642
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911047707.7A Active CN110886627B (en) | 2019-10-30 | 2019-10-30 | Integrated casing for combined engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110886627B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN118111119A (en) * | 2024-04-29 | 2024-05-31 | 西安交通大学 | Hot fluid guiding device for combustion-heat exchange integrated helium heater of space engine |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1075973A (en) * | 1965-04-08 | 1967-07-19 | Fleur Corp | Improvements in or relating to turbines, rotary compressors and the like |
| CN105065143A (en) * | 2015-08-10 | 2015-11-18 | 广西玉柴机器股份有限公司 | Mixer |
| CN105257428A (en) * | 2015-11-06 | 2016-01-20 | 西南科技大学 | Distributed compression and cyclone ramjet engine |
| CN109372657A (en) * | 2018-08-31 | 2019-02-22 | 西安航天动力研究所 | A kind of novel precooled air combined engine |
-
2019
- 2019-10-30 CN CN201911047707.7A patent/CN110886627B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1075973A (en) * | 1965-04-08 | 1967-07-19 | Fleur Corp | Improvements in or relating to turbines, rotary compressors and the like |
| CN105065143A (en) * | 2015-08-10 | 2015-11-18 | 广西玉柴机器股份有限公司 | Mixer |
| CN105257428A (en) * | 2015-11-06 | 2016-01-20 | 西南科技大学 | Distributed compression and cyclone ramjet engine |
| CN109372657A (en) * | 2018-08-31 | 2019-02-22 | 西安航天动力研究所 | A kind of novel precooled air combined engine |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN118111119A (en) * | 2024-04-29 | 2024-05-31 | 西安交通大学 | Hot fluid guiding device for combustion-heat exchange integrated helium heater of space engine |
Also Published As
| Publication number | Publication date |
|---|---|
| CN110886627B (en) | 2022-07-29 |
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