CN111692134B - Backflow type compressor and engine thereof - Google Patents
Backflow type compressor and engine thereof Download PDFInfo
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- CN111692134B CN111692134B CN202010587570.0A CN202010587570A CN111692134B CN 111692134 B CN111692134 B CN 111692134B CN 202010587570 A CN202010587570 A CN 202010587570A CN 111692134 B CN111692134 B CN 111692134B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
- F04D29/541—Specially adapted for elastic fluid pumps
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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
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
- F02C3/06—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
Abstract
The invention discloses a reflux compressor and an engine thereof, comprising a U-shaped sleeve rotor, wherein the U-shaped sleeve rotor comprises an inner cylinder, an outer cylinder and an annular cylinder bottom connected between the inner cylinder and the outer cylinder; an end cover is arranged on the opening side of the U-shaped sleeve rotor, and an inner duct stator and an outer duct stator are arranged between the end cover and the U-shaped sleeve rotor, wherein the inner duct stator is arranged in the middle of the inner cylinder, and the outer duct stator is arranged between the inner cylinder and the outer cylinder; a low-pressure air compression section is formed between the inner cylinder and the inner duct stator; a high-pressure air compression section is formed between the inner cylinder and the outer ducted stator; the air flow flows back to the high-pressure air compression section after passing through the low-pressure air compression section, and then flows back again and is discharged; the invention can improve the air compression capacity of the air compressor, further improve the power of the engine and shorten the axial size of the engine.
Description
Technical Field
The invention relates to the field of engines, in particular to a backflow type compressor and an engine thereof.
Background
With the continuous development of the aviation industry, the performance of airplanes is more excellent, and the requirements on the performance of engines are also the water rising ship height. In order to meet the requirement of higher power of an engine, the air compression capacity, particularly the efficiency, of an engine compressor is inevitably improved. The main development directions of the existing compressor are as follows: the number of stages of the gas compressor is increased, the single-stage gas compression ratio is improved, the rotating speed of the bearing is improved, and the multi-stage bearing is realized.
However, the number of stages of the compressor is increased, so that parts are increased, and the overall reliability of the compressor is greatly weakened while the axial size is increased; the improvement of the single-stage compression ratio has quite high requirements on the improvement of the performance of the blade material; the rotating speed of the bearing is improved, so that not only is high requirement on bearing materials, but also more strict performance requirement on the compression efficiency of the blade at higher speed is provided; as regards the realisation of the multi-stage bearing, although this makes the cooperation between the compressors more efficient, it also increases the mechanical complexity, causing a considerable reduction in the overall reliability, which is not favourable for maintenance, and in addition, the above development tends to aggravate the problems in terms of cooling of the compressors to a greater or lesser extent.
Disclosure of Invention
The invention aims to provide a backflow type air compressor and an engine thereof, which are used for solving the problems in the prior art, improving the air compression capacity of the air compressor, further improving the power of the engine and shortening the axial size of the engine.
In order to achieve the purpose, the invention provides the following scheme:
the invention provides a backflow type compressor, which comprises a U-shaped sleeve rotor, wherein the U-shaped sleeve rotor comprises an inner cylinder, an outer cylinder and an annular cylinder bottom connected between the inner cylinder and the outer cylinder;
an end cover is arranged on the opening side of the U-shaped sleeve rotor, and an inner duct stator and an outer duct stator are arranged between the end cover and the U-shaped sleeve rotor, wherein the inner duct stator is arranged in the middle of the inner cylinder, and the outer duct stator is arranged between the inner cylinder and the outer cylinder;
a low-pressure air compression section is formed between the inner cylinder and the inner duct stator; a high-pressure air compression section is formed between the inner cylinder and the outer ducted stator; and the air flow flows back to the high-pressure air compression section after passing through the low-pressure air compression section, and then flows back again and is discharged.
Preferably, the end cover comprises an inner ring, an outer ring and an annular bulge connected between the inner ring and the outer ring, the inner ring is connected with the end of the inner ducted stator, the outer ring is connected with the end of the outer ducted stator, and the inner side of the annular bulge forms a backflow space for the air flow to enter the high-pressure air compression section from the low-pressure air compression section.
Preferably, the air flow path through which the air flow circulates is S-shaped, and the space of the air flow path gradually decreases from the inlet to the first corner and from the first corner to the second corner, and the second corner forms an enlarged arc-shaped space which gradually increases from the arc-shaped space to the outlet.
Preferably, the inner side of the annular cylinder bottom is provided with an outer duct stator connecting part, and the outer duct stator connecting part is rotatably connected with the outer duct stator; the low-pressure movable blade group arranged on the inner wall of the inner barrel is provided with an inner duct stator connecting part, and the inner duct stator connecting part is rotatably connected with the inner duct stator.
Preferably, the inner duct stator connecting part is provided in the middle of the low-pressure moving blade group of the first stage and the last stage.
Preferably, the endoprosthesis stator is a hollow conical structure, and an opening is formed in one end of the endoprosthesis stator.
The invention also provides an engine, wherein the backflow type compressor is applied, the inner side of the annular cylinder bottom is provided with a combustion chamber, and a turbine exhaust section is formed between the outer cylinder and the outer duct stator.
Preferably, the outer bottom surface of the annular cylinder bottom is provided with a fairing connecting part, and the fairing connecting part is rotatably connected with the fairing.
Preferably, the fairing is fixedly connected with the inner duct stator, and the fairing is also fixedly connected with the outer ring.
Compared with the prior art, the invention has the following technical effects:
(1) the engine rotor is set to be a U-shaped sleeve rotor and is matched with the inner duct stator and the outer duct stator, so that airflow entering the engine is converted twice in the axial direction, the airflow speed can be reduced, the static pressure is increased, the air compression capacity of the air compressor is improved during the first conversion, the airflow speed is further slowed down during the second conversion, turbulence can be generated, and stable and sufficient combustion of fuel oil in a combustion chamber is facilitated;
(2) according to the invention, the traditional low-pressure compressor rotor and the traditional high-pressure compressor rotor are combined and reformed into the U-shaped sleeve rotor, so that the axial size of the engine is greatly shortened, and the engine can be vertically arranged in a place with a smaller axis space inside the helicopter;
(3) the high-pressure compressor and the low-pressure compressor are designed in a layered mode, namely a high-pressure air compression section and a low-pressure air compression section are designed in a layered mode, the high-pressure air compression section and the low-pressure air compression section are separated into an inner duct and an outer duct, and due to the fact that the rotating radiuses are different and the linear speeds are different, the function that the rotating speeds of the high-pressure compressor and the low-pressure compressor are different and can be achieved by a multi-stage bearing is partially achieved on;
(4) according to the invention, the high-pressure air compressing section is arranged at the outer side of the low-pressure air compressing section, and the low-pressure moving blades of the low-pressure air compressing section are assembled on the inner wall of the inner cylinder of the U-shaped sleeve rotor, so that the axial stress directions of the high-pressure moving blade group and the low-pressure moving blade group are completely opposite although the rotating directions of the high-pressure moving blade group and the low-pressure moving blade group are the same, and the axial stress of the whole air compressing section can be counteracted to a;
(5) compared with the axial distance from the turbine of the conventional axial-flow double-shaft turbojet engine to the stress center of the gas compressor, the axial distance from the turbine moving blade set to the stress center of the high-pressure and low-pressure gas compression section is greatly reduced, so that the torsional deformation of the U-shaped sleeve rotor is also greatly reduced, and the slippage phenomenon of the U-shaped sleeve rotor is avoided as much as possible;
(6) the radial radius size is increased, so that the space for arranging cooling systems of all parts is more, the heat-resistant protection of the whole engine can be better, and the service life of the engine can be longer.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed to be used in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings without inventive exercise.
FIG. 1 is a schematic structural diagram of a conventional axial-flow twin-shaft turbojet engine;
FIG. 2 is an exploded view of the compressor/engine components of the present invention;
FIG. 3 is a cross-sectional view of a compressor/engine assembly of the present invention;
FIG. 4 is a schematic view of the engine structure and airflow path of the present invention;
FIG. 5 is a schematic sectional view of a rotor with a U-shaped sleeve according to the present invention;
FIG. 6 is a cross-sectional view of the stator structure of the endoprosthesis according to the present invention;
FIG. 7 is a schematic view of a fairing according to the present invention;
wherein, 1, a U-shaped sleeve rotor; 11. a low pressure moving blade group; 12. a high pressure moving blade group; 13. a turbine moving blade group; 14. an outer duct stator connection; 15. an inner duct stator connection; 16. a cowl connecting portion; 2. an outer ducted stator; 21. a high-pressure static blade group; 22. a turbine stator vane set; 3. an inner ducted stator; 31. a low pressure static vane set; 4. an end cap; 5. a cowling; 6. a low-pressure gas compression section; 7. a high-pressure air compression section; 8. a turbine exhaust section; 9. a combustion chamber; 10. an air flow path; 101. a low pressure compressor rotor; 102. a high pressure compressor rotor; 103. a combustion chamber; 104. a high pressure turbine; 105. a low pressure turbine; 106. an air flow path.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The invention aims to provide a backflow type air compressor and an engine thereof, which are used for solving the problems in the prior art, improving the air compression capacity of the air compressor, further improving the power of the engine and shortening the axial size of the engine.
In order to make the aforementioned objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in further detail below.
The invention provides a reflux compressor, which comprises a U-shaped sleeve rotor 1, as shown in figure 5, wherein the U-shaped sleeve rotor 1 comprises an inner cylinder, an outer cylinder and an annular cylinder bottom connected between the inner cylinder and the outer cylinder, and the connection relationship of the inner cylinder, the outer cylinder and the annular cylinder bottom can be integrally formed, or the annular cylinder bottom can be connected to the end parts of the inner cylinder and the outer cylinder through the existing connection mode (such as a bolt connection mode); the inner wall of the inner cylinder is provided with a low-pressure moving blade set 11, the outer wall of the inner cylinder is provided with a high-pressure moving blade set 12, the inner wall of the outer cylinder is provided with a turbine moving blade set 13 (when the inner cylinder is used as a compressor, the turbine moving blade set 13 is not arranged), it needs to be explained that the key point of the invention is not the improvement of the blade structure, the arrangement of all blades related to the invention is based on the prior art, wherein the low-pressure moving blade set 11 and the high-pressure moving blade set 12 are respectively equivalent to a low-pressure compressor moving blade set and a high-pressure compressor moving blade set in the prior art, the invention is only correspondingly modified in adaptability, and the modification can be known by technicians in the field; as shown in fig. 3 to 4, a space for accommodating the outer ducted stator 2 is formed between the inner cylinder and the outer cylinder, a space for accommodating the inner ducted stator 3 is formed in the middle of the inner cylinder, and an arc-shaped space for accommodating the combustion chamber 9 is formed inside the annular cylinder bottom.
As shown in fig. 2-3, the device further comprises an inner ducted stator 3, an outer ducted stator 2 and an end cover 4 arranged on the opening side of the U-shaped sleeve rotor 1; wherein, the inner ducted stator 3 is arranged in the middle of the inner cylinder, and the outer ducted stator 2 is arranged between the inner cylinder and the outer cylinder; u type sleeve rotor 1 is movable part, and outer duct stator 2, inner duct stator 3 and end cover 4 are fixed part, and outer duct stator 2, inner duct stator 3 and end cover 4 also play the effect of constituteing air current passageway when playing bearing structure.
Referring to fig. 2, the bypass stator 2 is a cylindrical structure, and the inner wall thereof is provided with a high-pressure static blade group 21, and the outer wall thereof is provided with a turbine static blade group 22 (when the bypass stator is used as a compressor, the turbine static blade group 22 may not be provided); referring to fig. 6, the outer wall of the endoprosthesis stator 3 is further provided with a low-pressure static blade group 31; it should be noted that, as is clear from the above description, the arrangement of all the blades according to the present invention is based on the prior art, and the high-pressure stationary blade group 21, the turbine stationary blade group 22, and the low-pressure stationary blade group 31 are also adaptively adjusted based on the prior art.
As shown in fig. 3, an end cover 4 is arranged on the opening side of the U-shaped sleeve rotor 1, an inner ducted stator 3 and an outer ducted stator 2 are arranged between the end cover 4 and the U-shaped sleeve rotor 1, wherein the inner ducted stator 3 is arranged in the middle of the inner cylinder, and the outer ducted stator 2 is arranged between the inner cylinder and the outer cylinder;
as shown in fig. 4, a low-pressure air compressing section 6 is formed between the inner cylinder and the inner ducted stator 3; a high-pressure air compression section 7 is formed between the inner cylinder and the outer ducted stator 2; the air flow flows back to the high-pressure air compression section 7 after passing through the low-pressure air compression section 6, and then flows back again and is discharged.
As shown in fig. 4, the U-shaped sleeve rotor 1 is divided into S-shaped air flow paths 10 after being engaged with the outer duct stator 2 and the inner duct stator 3, the air flow paths 10 are gradually reduced from the inlet to the first corner and from the first corner to the second corner, and the second corner forms an enlarged arc-shaped space (for forming the combustion chamber 9 in the engine) and is gradually enlarged from the arc-shaped space to the outlet.
Referring again to fig. 5, the inner side of the annular cylinder bottom of the U-shaped sleeve rotor 1 is provided with an outer duct stator connecting part 14, and it is noted that the outer duct stator connecting part 14 has a certain distance from the inside of the annular cylinder bottom to form an arc-shaped space for accommodating the combustion chamber 9; the low-pressure moving blade group 11 is provided at a middle portion thereof with an inner-duct stator connection portion 15 (see specifically described later).
Further, the inner duct stator connecting portion 15 is provided on the inner ring in the middle of the first-stage and last-stage low-pressure moving blade group 11.
The invention also provides an engine using the backflow type compressor.
As shown in fig. 4, a low-pressure air compression section 6 is formed between the inner cylinder of the U-shaped sleeve rotor 1 and the inner duct stator 3; a high-pressure air compression section 7 is formed between the inner cylinder of the U-shaped sleeve rotor 1 and the outer ducted stator 2; a turbine exhaust section 8 is formed between the outer cylinder of the U-shaped sleeve rotor 1 and the outer ducted stator 2; a combustion chamber 9 is arranged on the inner side of the annular cylinder bottom of the U-shaped sleeve rotor 1;
as shown in fig. 4, the air flow flows back to the high-pressure air compression section 7 after passing through the low-pressure air compression section 6, and then enters the turbine exhaust section 8 after passing through the combustion chamber 9, and simultaneously drives the U-shaped sleeve rotor 1 to rotate, that is, the air flow path 10 forms an S-shape, the U-shaped sleeve rotor 1 is matched with the inner duct stator 3, the outer duct stator 2 and the end cover 4, so that the air flow entering the engine is converted twice in the axial direction, during the first conversion, the air flow velocity can be reduced, the static pressure is increased, the air compression capability of the air compressor is improved, during the second conversion, the air flow velocity is further slowed down, and turbulence can be generated, which is beneficial to stable and sufficient combustion of fuel oil in the combustion chamber 9.
As shown in fig. 5, and referring to fig. 3-4, the inside of the annular cylinder bottom of the U-shaped sleeve rotor 1 is provided with an outer ducted stator connecting portion 14, and the outer ducted stator connecting portion 14 is rotatably connected with the outer ducted stator 2, for example, by means of a sliding bearing; the low-pressure moving blade group 11 is provided with an inner duct stator connecting portion 15 at the middle portion, the inner duct stator connecting portion 15 is rotatably connected with the inner duct stator 3, for example, the connection manner of a sliding bearing, it should be noted that the low-pressure moving blade group 11 is provided with multiple stages, and in order to ensure the reliability of the rotational connection, the inner duct stator connecting portion 15 is preferably provided at the first stage and the last stage.
As shown in fig. 6, further, the end of the inner ducted stator 3 that the air current impacts is set into an arc shape, the air current can be guided to enter the low-pressure air compressing section 6, the inner ducted stator 3 is of a hollow conical structure, an opening is formed in the reverse end of the inner ducted stator 3 that the air current impacts, the extra weight can be reduced, and the engine can reach the design requirement of light weight.
As shown in fig. 2 and 3, the end cap 4 includes an inner ring, an outer ring and an annular protrusion connected between the inner ring and the outer ring, the inner ring is connected with one end of the inner ducted stator 3 with an opening, the outer ring is connected with one end of the outer ducted stator 2, wherein the connection modes are all the prior art, as the bolt connection commonly used in the prior art, referring to fig. 4, the inner side of the annular protrusion of the end cap 4 forms a backflow space for the low-pressure air compression section 6 to enter the high-pressure air compression section 7, and in addition, wedge grooves for positioning are further arranged on the inner ring and the outer ring of the end cap 4.
As shown in fig. 5, the cowling connecting portion 16 is disposed on the outer bottom surface of the annular cylinder bottom of the U-shaped sleeve rotor 1, and the cowling connecting portion 16 is rotatably connected to the cowling 5, as shown in fig. 4, the connection mode may be in the form of a sliding bearing, it should be noted that the sliding bearing may be disposed in a whole along the annular shape or in a plurality of sliding bearings may be disposed along the annular shape, and at this time, the cowling 5 may achieve the effect of limiting the axial displacement of the U-shaped sleeve rotor 1.
As shown in fig. 7, and referring to fig. 2-4, the end of the fairing 5 facing the air flow is provided with three supporting structures, the center of the structure is provided with a first ring, the first ring can be sleeved on the arc structure at the front end of the inner ducted stator 3 to form a support for the fairing 5, in addition, referring to fig. 3, the other end of the fairing 5 is provided with a multiple supporting structure, the center of the structure is provided with a larger second ring, the second ring is fixedly connected with the outer ring of the end cover 4 to form a support for the other side of the fairing 5, finally, a stable supporting structure for the fairing 5 is formed, and the fairing 5 can play a role in improving the strength of the whole structure of the engine and reducing the resistance.
The working principle of the engine is as follows: as shown in fig. 4, the air flow enters the low-pressure air compressing section 6 to complete the compression in the first stage, then the air flow passes through the space formed inside the annular protrusion of the end cover 4, so that the air flow flows back to the high-pressure air compressing section 7 from the low-pressure air compressing section 6, and the backflow compression process from backward flow to forward flow is completed, which is the compression in the second stage, and then the air flow enters the high-pressure air compressing section 7 to complete the compression in the third stage, and finally the air flow enters the combustion chamber 9 located inside the annular cylinder bottom of the U-shaped sleeve rotor 1 to complete the combustion supporting process, and pushes the turbine moving blade set 13 inside the outer cylinder of the U-shaped sleeve rotor 1 to do work, so that the U-shaped sleeve rotor 1 rotates, and finally the air flow leaves the engine through the turbine exhaust section 8; the high-pressure compressor and the low-pressure compressor are designed in a layered mode, namely the high-pressure air compression section 7 and the low-pressure air compression section 6 are designed in a layered mode and are separated into an inner duct and an outer duct, although the angular velocities of the high-pressure movable blade group 12 and the low-pressure movable blade group 11 are the same and rotate around the same shaft, the blades are respectively assembled on the inner wall and the outer wall of the inner cylinder of the U-shaped sleeve rotor 1, the average radius of the blades from the rotating shaft is different, the linear velocity is obviously different, the specific linear velocity difference of each stage of movable blades can be adjusted according to actual requirements by designing the radius of the rotating shaft, and therefore the high-pressure compressor and the low-pressure compressor can achieve the function of different rotating speeds of the high-pressure compressor and the low-pressure compressor partially on the.
The principle and the implementation mode of the invention are explained by applying a specific example, and the description of the embodiment is only used for helping to understand the method and the core idea of the invention; meanwhile, for a person skilled in the art, according to the idea of the present invention, the specific embodiments and the application range may be changed. In view of the above, the present disclosure should not be construed as limiting the invention.
Claims (9)
1. A backflow type compressor is characterized in that: the U-shaped sleeve rotor comprises an inner sleeve, an outer sleeve and an annular sleeve bottom connected between the inner sleeve and the outer sleeve; the inner wall of the inner cylinder is provided with a low-pressure movable blade group, and the outer wall of the inner cylinder is provided with a high-pressure movable blade group;
an end cover is arranged on the opening side of the U-shaped sleeve rotor, and an inner duct stator and an outer duct stator are arranged between the end cover and the U-shaped sleeve rotor, wherein the inner duct stator is arranged in the middle of the inner cylinder, and the outer duct stator is arranged between the inner cylinder and the outer cylinder;
a low-pressure air compression section is formed between the inner cylinder and the inner duct stator; a high-pressure air compression section is formed between the inner cylinder and the outer ducted stator; and the air flow flows back to the high-pressure air compression section after passing through the low-pressure air compression section, and then flows back again and is discharged.
2. The recirculation compressor of claim 1, wherein: the end cover comprises an inner ring, an outer ring and an annular bulge connected between the inner ring and the outer ring, the inner ring is connected with the end of the inner ducted stator, the outer ring is connected with the end of the outer ducted stator, and the inner side of the annular bulge forms a backflow space for the air flow to enter the high-pressure air compression section from the low-pressure air compression section.
3. The recirculation compressor of claim 2, wherein: the air flow path of the air flow is S-shaped, the space of the air flow is gradually reduced from the inlet to the first corner and from the first corner to the second corner, an expanded arc-shaped space is formed at the second corner, and the space is gradually expanded from the arc-shaped space to the outlet.
4. The recirculation compressor of claim 2, wherein: the inner side of the annular cylinder bottom is provided with an outer ducted stator connecting part, and the outer ducted stator connecting part is rotatably connected with the outer ducted stator; the low-pressure movable blade group arranged on the inner wall of the inner barrel is provided with an inner duct stator connecting part, and the inner duct stator connecting part is rotatably connected with the inner duct stator.
5. The recirculation compressor of claim 4, wherein: the inner duct stator connecting part is arranged in the middle of the low-pressure movable blade group of the first stage and the last stage.
6. The recirculation compressor according to any one of claims 1 to 5, characterized in that: the inner duct stator is of a hollow conical structure, and an opening is formed in one end of the inner duct stator.
7. An engine, characterized in that: the backflow type compressor as claimed in any one of claims 1 to 6 is applied, a combustion chamber is arranged on the inner side of the annular cylinder bottom, and a turbine exhaust section is formed between the outer cylinder and the outer ducted stator.
8. The engine of claim 7, wherein: the outer bottom surface of annular section of thick bamboo bottom is provided with the radome fairing connecting portion, radome fairing connecting portion rotatable coupling has the radome fairing.
9. The engine of claim 8, wherein: the fairing is fixedly connected with the inner duct stator, the end cover comprises an inner ring, an outer ring and an annular bulge connected between the inner ring and the outer ring, and the fairing is fixedly connected with the outer ring.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202010587570.0A CN111692134B (en) | 2020-06-24 | 2020-06-24 | Backflow type compressor and engine thereof |
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| CN202010587570.0A CN111692134B (en) | 2020-06-24 | 2020-06-24 | Backflow type compressor and engine thereof |
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| CN111692134A CN111692134A (en) | 2020-09-22 |
| CN111692134B true CN111692134B (en) | 2021-06-15 |
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| CN114427546A (en) * | 2022-01-21 | 2022-05-03 | 中国航发沈阳发动机研究所 | Adjustable stator blade and casing structure |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6397577B1 (en) * | 2001-04-02 | 2002-06-04 | The United States Of America As Represented By The Secretary Of The Air Force | Shaftless gas turbine engine spool |
| CN105422314A (en) * | 2015-12-29 | 2016-03-23 | 西北工业大学 | Coaxial lifting turbojet engine |
| CN105508081A (en) * | 2015-12-29 | 2016-04-20 | 西北工业大学 | Coaxial turbo-shaft engine |
| CN108825380A (en) * | 2018-05-28 | 2018-11-16 | 华中科技大学 | A kind of high efficiency turboshaft engine |
| CN208565013U (en) * | 2018-08-15 | 2019-03-01 | 浙江伟康电机有限公司 | A kind of small size axial flow blower of low noise high speed |
-
2020
- 2020-06-24 CN CN202010587570.0A patent/CN111692134B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6397577B1 (en) * | 2001-04-02 | 2002-06-04 | The United States Of America As Represented By The Secretary Of The Air Force | Shaftless gas turbine engine spool |
| CN105422314A (en) * | 2015-12-29 | 2016-03-23 | 西北工业大学 | Coaxial lifting turbojet engine |
| CN105508081A (en) * | 2015-12-29 | 2016-04-20 | 西北工业大学 | Coaxial turbo-shaft engine |
| CN108825380A (en) * | 2018-05-28 | 2018-11-16 | 华中科技大学 | A kind of high efficiency turboshaft engine |
| CN208565013U (en) * | 2018-08-15 | 2019-03-01 | 浙江伟康电机有限公司 | A kind of small size axial flow blower of low noise high speed |
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