CN103867235A - Tubular vortex reducer air inducing system - Google Patents
Tubular vortex reducer air inducing system Download PDFInfo
- Publication number
- CN103867235A CN103867235A CN201210552768.0A CN201210552768A CN103867235A CN 103867235 A CN103867235 A CN 103867235A CN 201210552768 A CN201210552768 A CN 201210552768A CN 103867235 A CN103867235 A CN 103867235A
- Authority
- CN
- China
- Prior art keywords
- scroll
- subtract
- subtracts
- entrance
- tubular type
- 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.)
- Granted
Links
Images
Classifications
-
- 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
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Rotary Pumps (AREA)
Abstract
The invention provides a tubular vortex reducer air inducing system for an aero-engine. The tubular vortex reducer air inducing system comprises an air compressor right disc (1), an air compressor left disc (2) and a supporting ring (7), wherein the air compressor right disc (1) and the air compressor left disc (2) form an air compressor disc chamber, and the supporting ring (7) is fixedly connected with the air compressor right disc (1); a plurality of vortex reducing tubes (4) are distributed in the air compressor disc chamber in a radial manner and are fixedly arranged on the supporting ring (7); the circumferential deflection angle of an entrance segment (401) of each vortex reducing tube (4) is alpha, and the angle alpha is equal to an included angle of the relative velocity direction of entrance airflow of each vortex reducing tube (4) and the radial direction of a fixed position of the corresponding vortex reducing tube (4). According to the tubular vortex reducer air inducing system, the airflow entrance segments of the vortex reducing tubes are designed to circumferential deflected forms so as to exactly face to airflow directions, thus, the pressure loss can be effectively reduced, and the cooling and air supplying pressure of an aero-engine air system are guaranteed.
Description
Technical field
The present invention relates to aero engine technology field, particularly in engine air system, subtract the design of whirlpool device bleed stream.
Background technique
One of target of the bleed flow path designs of aeroengine air system is pressure and the pressure of obturaging that reduces the pressure loss, ensures the cooling air feed of high-temperature component.
Traditional bleed air system realizes by exterior line is set, and this has all brought adverse effect to engine weight and exterior line layout.Present stage, comparatively advanced motor adopted the form of gas compressor drum barrel perforate to realize inner bleed, had avoided these unfavorable factors.But, in inner bleed process, because the high radial location in gas from gas compressor dish chamber flows to low radial location, free vortex development is violent, cause flow losses larger, the mode that subtracts whirlpool device by installation can effectively weaken the violent development of eddy current, thereby reduces the pressure loss.The design that subtracts thus whirlpool device has a certain impact for modern aeroengine performance tool.
Patent documentation US7086830 discloses a kind of tubular type and has subtracted whirlpool device structure, this structure directly the gas of gas compressor sprue introduce subtract scroll after until in center cavity, this mode makes to subtract scroll inlet end and fixes, cause air-flow to arrive in center cavity with forced vortex state, flow losses are larger than the transition status from free vortex to forced vortex.Patent documentation US7159402 discloses another kind of tubular type and has subtracted whirlpool device structure, and this subtracts whirlpool device inlet end is cantilever structure, and than being directly installed on, drum barrel place (US7086830) pressure loss is little.But these existing tubular types subtract whirlpool device still can not be satisfactory to the effect that reduces the pressure loss.
Summary of the invention
The present invention has proposed a kind of new whirlpool device bleed air system form that subtracts on the basis of existing technology, has taken into full account aerodynamic characteristic, can realize the object that reduces flow losses.
Tubular type for aeroengine according to the present invention subtracts whirlpool device bleed air system and comprises and form the right dish of gas compressor, the left dish of gas compressor in compressor disc chamber and the support ring being connected and fixed with the right dish of described gas compressor, multiple scrolls that subtract are radially arranged in compressor disc chamber and are fixed on described support ring, wherein, the described entrance that subtracts scroll is along circumferential deflection angle [alpha], the inlet air flow relative velocity direction that described angle [alpha] equals to subtract scroll and the angle of radial direction at fixed position place that subtracts scroll.
According to a kind of mode of execution, in the time subtracting the circumferential speed of scroll described in inlet air flow circumferential speed is less than, subtract the described entrance of scroll to engine rotor sense of rotation deflection angle α.
According to another kind of mode of execution, in the time subtracting the circumferential speed of scroll described in inlet air flow circumferential speed is greater than, subtract the described entrance of scroll in contrast to engine rotor sense of rotation deflection angle α.
Advantageously, described angle [alpha] is 5 °～85 °.More preferably, described angle [alpha] is 10 °～80 °.Best, described angle [alpha] is 15 °～75 °.
Further, the entrance section that subtracts scroll described in is vertical with inlet air flow relative velocity direction.
Further, the outer surface that subtracts the entrance of scroll described in is the closed surface being made up of curve.
Alternatively, the outer surface that subtracts the entrance of scroll described in is the closure plane being made up of straight line.
Tubular type of the present invention subtract whirlpool device bleed air system from reduce air-flow enter subtract scroll produce local losses start with, formed by circumferential component velocity, radial velocity component, axial component velocity owing to subtracting device ingress, whirlpool airspeed, and axially component velocity is little more a lot of than other direction component velocities, substantially can not consider, so air-flow is mainly the resultant velocity of relatively circumferential component velocity and radial velocity component formation under relative coordinate system, has certain angle with radial direction.Subtract scroll in order to ensure that air-flow can enter comparatively smoothly, by the entrance that subtracts scroll be designed to circumferentially to some extent the form of deflection with just to airflow direction, can effectively reduce the pressure loss, ensured the cooling supply gas pressure of aeroengine air system.
Brief description of the drawings
Further feature of the present invention and advantage will be understood better by the embodiment of describing in detail below in conjunction with accompanying drawing, in accompanying drawing, and the same or analogous parts of identical designated, wherein:
Fig. 1 is the perspective schematic view that the tubular type for aeroengine subtracts whirlpool device bleed air system structure according to the present invention;
Fig. 2 removes the perspective schematic view that scroll is arranged in compressor disc chamber that subtracts illustrating after the left dish of gas compressor;
Fig. 3 subtracts the sectional view of scroll mounting structure in axial-radial plane;
Fig. 4 is the sectional view along Fig. 3 center line A-A, shows the inlet air flow circumferential speed that subtracts scroll and is less than the entrance structure that subtracts scroll in the situation that subtracts scroll circumferential speed;
Fig. 5 be shown in Fig. 4 in situation according to the schematic diagram of the entrance structure that subtracts scroll of another kind of preferred implementation;
Fig. 6 is the sectional view along Fig. 3 center line A-A, shows the inlet air flow circumferential speed that subtracts scroll and is greater than the entrance structure that subtracts scroll in the situation that subtracts scroll circumferential speed;
Fig. 7 be shown in Fig. 6 in situation according to the schematic diagram of the entrance structure that subtracts scroll of another kind of preferred implementation.
Description of reference numerals
The left dish of right dish 2 gas compressor of 1 gas compressor
3 drum barrel holes 4 subtract scroll
401 entrance 5 drum barrel axles
7 support ring 8 running shafts
101 tangent directions 102 subtract scroll radial direction
103 subtract scroll geometric center lines 104 subtracts scroll entrance section
Embodiment
Describe enforcement and the use of specific embodiments of the invention below in detail.But, should be appreciated that described specific embodiment only exemplarily illustrates and implements and use special type of the present invention, but not limit the scope of the invention.
First referring to Fig. 1 to 3, the whole whirlpool device bleed air system that subtracts is rotated around running shaft 8, and sense of rotation as shown by arrows.Shown in subtract whirlpool device bleed air system and comprise and form the right dish 1 of gas compressor, the left dish 2 of gas compressor in compressor disc chamber and the support ring 7 being connected and fixed with the right dish 1 of described gas compressor, multiple scrolls 4 that subtract are radially arranged in compressor disc chamber and by snap ring and are fixed on support ring 7, and described support ring 7 examples are connected and fixed by bolt and the right dish 1 of described gas compressor as shown in Figure 3.The air-flow of gas compressor mainstream channel is after stator, part air-flow enters compressor disc chamber by the long-round-shape drum barrel hole 3 on drum barrel axle 5, and with the form of free vortex radially axis direction flow, gas is by subtracting scroll 4 subsequently, enter in chamber, axle center with the form of forced vortex, this has just realized and has subtracted whirlpool device bleed.
In order effectively to reduce stream pressure loss, the present invention by the entrance 401 that subtracts scroll 4 along angle [alpha] of circumferential deflection with just to airflow direction, the inlet air flow relative velocity direction that this angle [alpha] equals to subtract scroll 4 and the angle of radial direction at fixed position place that subtracts scroll 4.
Specifically, air-flow enters compressor disc chamber, subtracts before scroll 4 entering, if air-flow circumferential speed subtracts in the situation of circumferential speed of scroll 4 described in being less than, referring to Fig. 4 and Fig. 5, subtract the entrance 401 of scroll 4 to engine rotor sense of rotation (illustrating with arrow) deflection angle α.Angle [alpha] is subtract scroll geometric center lines 103 and subtract the tangent direction 101 at scroll entrance section 104 intersection point places and subtract the angle (being the angle of inlet air flow relative velocity direction and radial direction 102) between scroll radial direction 102.
According to another kind of mode of execution, when entering, air-flow subtracts before scroll 4, if air-flow circumferential speed is greater than in the situation of the circumferential speed that subtracts scroll 4, referring to Fig. 6 and Fig. 7, subtract the entrance 401 of scroll 4 in contrast to engine rotor sense of rotation (illustrating with arrow) deflection angle α.
The span of above-mentioned angle [alpha] can be selected as required, for example, take from 5 °～85 °, is preferably 10 °～80 °, and the best is 15 °～75 °.
In addition, as shown in the figure, in order to ensure that air-flow enters effective admission area maximum while subtracting scroll 4, the entrance section 104 that subtracts scroll 4 is preferably vertical with tangent direction 101.
Should be understood that, although the scroll that subtracts according to the present invention in entrance place circumferential deflection, described in subtract scroll and remain by the continuous curved surface of curvature and form.For example, the outer surface that subtracts the entrance 401 of scroll 4 can be the closed surface being made up of curve as shown in Figure 4 and Figure 5, also can be the closure plane being made up of straight line as shown in Figure 6 and Figure 7.In any case, need to ensure that the entrance 401 that subtracts scroll 4 is to subtracting the intermediate section of scroll 4 until subtract the outlet section curvature of curved surface continuous transition of scroll 4.
Below disclose technology contents of the present invention and technical characterstic by specific embodiment; but be appreciated that; under creative ideas of the present invention; those skilled in the art can make various changes and improve the combination of above-mentioned disclosed various features and the feature clearly not illustrating at this, and these changes and improvements all belong to protection scope of the present invention.
Claims (9)
1. subtract whirlpool device bleed air system for the tubular type of aeroengine, comprise the right dish of gas compressor (1) that forms compressor disc chamber, the left dish of gas compressor (2) and the support ring (7) being connected and fixed with the right dish of described gas compressor (1), multiple scrolls (4) that subtract are radially arranged in compressor disc chamber and are fixed on described support ring (7), it is characterized in that, the described entrance (401) that subtracts scroll (4) is along circumferential deflection angle [alpha], the angle that described angle [alpha] equals to subtract the inlet air flow relative velocity direction of scroll (4) and subtracts the radial direction at the fixed position place of scroll (4).
2. tubular type according to claim 1 subtracts whirlpool device bleed air system, it is characterized in that, in the time subtracting the circumferential speed of scroll (4) described in air-flow circumferential speed is less than, subtract the described entrance (401) of scroll (4) to engine rotor sense of rotation deflection angle α.
3. tubular type according to claim 1 subtracts whirlpool device bleed air system, it is characterized in that, in the time subtracting the circumferential speed of scroll (4) described in air-flow circumferential speed is greater than, subtract the described entrance (401) of scroll (4) in contrast to engine rotor sense of rotation deflection angle α.
4. subtract whirlpool device bleed air system according to the tubular type described in claim 2 or 3, it is characterized in that, described angle [alpha] is 5 °～85 °.
5. tubular type according to claim 4 subtracts whirlpool device bleed air system, it is characterized in that, described angle [alpha] is 10 °～80 °.
6. tubular type according to claim 5 subtracts whirlpool device bleed air system, it is characterized in that, described angle [alpha] is 15 °～75 °.
7. tubular type according to claim 6 subtracts whirlpool device bleed air system, it is characterized in that, described in to subtract the entrance section of scroll (4) vertical with inlet air flow relative velocity direction.
8. tubular type according to claim 7 subtracts whirlpool device bleed air system, it is characterized in that, described in subtract the entrance (401) of scroll (4) outer surface be the closed surface being formed by curve.
9. tubular type according to claim 7 subtracts whirlpool device bleed air system, it is characterized in that, described in subtract the entrance (401) of scroll (4) outer surface be the closure plane being formed by straight line.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210552768.0A CN103867235B (en) | 2012-12-18 | 2012-12-18 | A kind of tubular type subtracts whirlpool device bleed air system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210552768.0A CN103867235B (en) | 2012-12-18 | 2012-12-18 | A kind of tubular type subtracts whirlpool device bleed air system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103867235A true CN103867235A (en) | 2014-06-18 |
| CN103867235B CN103867235B (en) | 2015-12-23 |
Family
ID=50906194
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201210552768.0A Active CN103867235B (en) | 2012-12-18 | 2012-12-18 | A kind of tubular type subtracts whirlpool device bleed air system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103867235B (en) |
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105201909A (en) * | 2014-06-25 | 2015-12-30 | 中航商用航空发动机有限责任公司 | Gas compressor and centripetal air entraining vortex reducing device thereof |
| CN105888849A (en) * | 2016-04-06 | 2016-08-24 | 中国南方航空工业(集团)有限公司 | Bleed air cooling structure and aeroengine with bleed air cooling structure |
| CN105402028B (en) * | 2015-04-30 | 2017-05-03 | 中国科学院工程热物理研究所 | Rib plate eddy flow control structure, rotation disk cavity system and gas turbine |
| EP3176367A1 (en) * | 2015-12-03 | 2017-06-07 | General Electric Company | Turbine discs and methods of fabricating the same |
| CN107218083A (en) * | 2017-06-21 | 2017-09-29 | 南京航空航天大学 | A kind of curved hole preswirl nozzle for structure of being prewhirled for cold air |
| CN111775177A (en) * | 2020-06-30 | 2020-10-16 | 大连海事大学 | Integrated valve-controlled modular double-acting hydraulic artificial muscle joint |
| CN112283156A (en) * | 2020-12-29 | 2021-01-29 | 中国航发上海商用航空发动机制造有限责任公司 | Gas compressor bleed structure and aeroengine |
| CN112377307A (en) * | 2020-10-28 | 2021-02-19 | 北京航空航天大学 | Curved tube type vortex reducing system with high-radius outlet |
| CN112412628A (en) * | 2020-11-27 | 2021-02-26 | 北京化工大学 | Closed type repeated cooling fluid network and closed loop terminal structure for gas turbine |
| CN113266599A (en) * | 2021-05-21 | 2021-08-17 | 西安交通大学 | Spindle-shaped air entraining structure for secondary air system of gas turbine |
| CN114718910A (en) * | 2021-01-06 | 2022-07-08 | 中国航发商用航空发动机有限责任公司 | Self-adaptive vector vortex reducer, high-pressure compressor and air entraining method of high-pressure compressor |
| CN114838006A (en) * | 2022-04-29 | 2022-08-02 | 北京航空航天大学 | Baffle type vortex-reducing air-entraining system for compressor |
| CN114961893A (en) * | 2021-02-24 | 2022-08-30 | 中国航发商用航空发动机有限责任公司 | Aeroengine vortex reducer air entraining device and aeroengine |
| CN115013549A (en) * | 2022-06-15 | 2022-09-06 | 北京航空航天大学 | Radial bleed air flow regulating system of compressor |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4236869A (en) * | 1977-12-27 | 1980-12-02 | United Technologies Corporation | Gas turbine engine having bleed apparatus with dynamic pressure recovery |
| FR2614654A1 (en) * | 1987-04-29 | 1988-11-04 | Snecma | Turbine engine axial compressor disc with centripetal air take-off |
| US6398487B1 (en) * | 2000-07-14 | 2002-06-04 | General Electric Company | Methods and apparatus for supplying cooling airflow in turbine engines |
| US20030101730A1 (en) * | 2001-12-05 | 2003-06-05 | Stefan Hein | Vortex reducer in the high-pressure compressor of a gas turbine |
| US20040179936A1 (en) * | 2003-03-12 | 2004-09-16 | Ian Fitzgerald | Tube-type vortex reducer with retaining ring |
| US20050172640A1 (en) * | 2004-02-11 | 2005-08-11 | Steffen Drevs | Tube-type vortex reducer |
| EP1978209A2 (en) * | 2007-03-26 | 2008-10-08 | Honeywell International Inc. | Vortex spoiler for delivery of cooling airflow in a turbine engine |
| US20090282834A1 (en) * | 2008-05-19 | 2009-11-19 | Stefan Hein | Combined Vortex reducer |
| RU2451840C2 (en) * | 2010-06-21 | 2012-05-27 | Открытое акционерное общество "Авиадвигатель" | Compressor rotor of gas-turbine engine |
-
2012
- 2012-12-18 CN CN201210552768.0A patent/CN103867235B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4236869A (en) * | 1977-12-27 | 1980-12-02 | United Technologies Corporation | Gas turbine engine having bleed apparatus with dynamic pressure recovery |
| FR2614654A1 (en) * | 1987-04-29 | 1988-11-04 | Snecma | Turbine engine axial compressor disc with centripetal air take-off |
| US6398487B1 (en) * | 2000-07-14 | 2002-06-04 | General Electric Company | Methods and apparatus for supplying cooling airflow in turbine engines |
| US20030101730A1 (en) * | 2001-12-05 | 2003-06-05 | Stefan Hein | Vortex reducer in the high-pressure compressor of a gas turbine |
| US20040179936A1 (en) * | 2003-03-12 | 2004-09-16 | Ian Fitzgerald | Tube-type vortex reducer with retaining ring |
| US20050172640A1 (en) * | 2004-02-11 | 2005-08-11 | Steffen Drevs | Tube-type vortex reducer |
| EP1978209A2 (en) * | 2007-03-26 | 2008-10-08 | Honeywell International Inc. | Vortex spoiler for delivery of cooling airflow in a turbine engine |
| US20090282834A1 (en) * | 2008-05-19 | 2009-11-19 | Stefan Hein | Combined Vortex reducer |
| RU2451840C2 (en) * | 2010-06-21 | 2012-05-27 | Открытое акционерное общество "Авиадвигатель" | Compressor rotor of gas-turbine engine |
Cited By (22)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105201909A (en) * | 2014-06-25 | 2015-12-30 | 中航商用航空发动机有限责任公司 | Gas compressor and centripetal air entraining vortex reducing device thereof |
| CN105402028B (en) * | 2015-04-30 | 2017-05-03 | 中国科学院工程热物理研究所 | Rib plate eddy flow control structure, rotation disk cavity system and gas turbine |
| CN106677903A (en) * | 2015-04-30 | 2017-05-17 | 中国科学院工程热物理研究所 | Ribbed plate vortex control structure, rotating disk chamber system and combustion gas turbine |
| CN106677903B (en) * | 2015-04-30 | 2018-07-20 | 中国科学院工程热物理研究所 | Floor control vortex structure, inside rotating disc cavities system, gas turbine |
| EP3176367A1 (en) * | 2015-12-03 | 2017-06-07 | General Electric Company | Turbine discs and methods of fabricating the same |
| US10584594B2 (en) | 2015-12-03 | 2020-03-10 | General Electric Company | Turbine discs and methods of fabricating the same |
| CN105888849A (en) * | 2016-04-06 | 2016-08-24 | 中国南方航空工业(集团)有限公司 | Bleed air cooling structure and aeroengine with bleed air cooling structure |
| CN107218083A (en) * | 2017-06-21 | 2017-09-29 | 南京航空航天大学 | A kind of curved hole preswirl nozzle for structure of being prewhirled for cold air |
| CN111775177B (en) * | 2020-06-30 | 2022-07-08 | 大连海事大学 | Integrated valve-controlled modular double-acting hydraulic artificial muscle joint |
| CN111775177A (en) * | 2020-06-30 | 2020-10-16 | 大连海事大学 | Integrated valve-controlled modular double-acting hydraulic artificial muscle joint |
| CN112377307A (en) * | 2020-10-28 | 2021-02-19 | 北京航空航天大学 | Curved tube type vortex reducing system with high-radius outlet |
| CN112412628A (en) * | 2020-11-27 | 2021-02-26 | 北京化工大学 | Closed type repeated cooling fluid network and closed loop terminal structure for gas turbine |
| CN112283156B (en) * | 2020-12-29 | 2021-03-19 | 中国航发上海商用航空发动机制造有限责任公司 | Gas compressor bleed structure and aeroengine |
| CN112283156A (en) * | 2020-12-29 | 2021-01-29 | 中国航发上海商用航空发动机制造有限责任公司 | Gas compressor bleed structure and aeroengine |
| CN114718910A (en) * | 2021-01-06 | 2022-07-08 | 中国航发商用航空发动机有限责任公司 | Self-adaptive vector vortex reducer, high-pressure compressor and air entraining method of high-pressure compressor |
| CN114718910B (en) * | 2021-01-06 | 2024-09-27 | 中国航发商用航空发动机有限责任公司 | Self-adaptive vector vortex reducer, high-pressure compressor and air entraining method of high-pressure compressor |
| CN114961893A (en) * | 2021-02-24 | 2022-08-30 | 中国航发商用航空发动机有限责任公司 | Aeroengine vortex reducer air entraining device and aeroengine |
| CN114961893B (en) * | 2021-02-24 | 2023-08-04 | 中国航发商用航空发动机有限责任公司 | Air entraining device of vortex breaker of aero-engine and aero-engine |
| CN113266599A (en) * | 2021-05-21 | 2021-08-17 | 西安交通大学 | Spindle-shaped air entraining structure for secondary air system of gas turbine |
| CN113266599B (en) * | 2021-05-21 | 2022-08-09 | 西安交通大学 | Spindle-shaped air-entraining structure for secondary air system of gas turbine |
| CN114838006A (en) * | 2022-04-29 | 2022-08-02 | 北京航空航天大学 | Baffle type vortex-reducing air-entraining system for compressor |
| CN115013549A (en) * | 2022-06-15 | 2022-09-06 | 北京航空航天大学 | Radial bleed air flow regulating system of compressor |
Also Published As
| Publication number | Publication date |
|---|---|
| CN103867235B (en) | 2015-12-23 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103867235B (en) | A kind of tubular type subtracts whirlpool device bleed air system | |
| EP2386723B1 (en) | Variable area turbine vane arrangement | |
| EP2256299B1 (en) | Deflector for a gas turbine strut and vane assembly | |
| JP5019721B2 (en) | Method and apparatus for assembling a gas turbine engine | |
| CN102221016B (en) | Compressor gas flow deflector and compressor incorporating the same | |
| US9534497B2 (en) | Inter-turbine ducts with variable area ratios | |
| US8882461B2 (en) | Gas turbine engines with improved trailing edge cooling arrangements | |
| EP2994647B1 (en) | Centrifugal compressor with inlet duct having swirl generators | |
| CN105402028A (en) | Rib plate eddy flow control structure, rotation disk cavity system and gas turbine | |
| EP2896787B1 (en) | Gas turbine | |
| EP2554793B1 (en) | Inter-turbine ducts with guide vanes of a gas turbine engine | |
| JP2019113070A (en) | Device for removing ice of separator nose of aircraft turbine engine | |
| CN102562184B (en) | Turbine shroud for air cycle machine, air cycle machine and assembling method thereof | |
| CN106812626B (en) | Contain casing outside a kind of engine | |
| US20190390554A1 (en) | Ventilated high pressure blade of a helicopter turbine comprising an upstream duct and a central cooling chamber | |
| CN107795342B (en) | Intermediate casing for a turbine wheel | |
| WO2014046832A1 (en) | Transition duct for use in a turbine engine and method of assembly | |
| CN203614465U (en) | Baffle mode eddy device of gas compressor and gas compressor | |
| EP3354848B1 (en) | Inter-turbine ducts with multiple splitter blades | |
| US20150132115A1 (en) | Unknown | |
| EP3450696B1 (en) | Segmented conduit with airfoil geometry | |
| US8784053B2 (en) | Fan shield and bearing housing for air cycle machine | |
| CN205277627U (en) | Miniature turbofan engine divides division exhaust apparatus with rectifier | |
| CN114439551B (en) | Aero-engine | |
| CN112283156B (en) | Gas compressor bleed structure and aeroengine |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CP03 | Change of name, title or address | ||
| CP03 | Change of name, title or address |
Address after: 200241 Minhang District Lianhua Road, Shanghai, No. 3998 Patentee after: China Hangfa commercial aviation engine limited liability company Address before: 201109 Shanghai city Minhang District Hongmei Road No. 5696 Room 101 Patentee before: AVIC Commercial Aircraft Engine Co.,Ltd. |