RU2010125468A - GAS TURBINE ENGINE COMPRESSOR ROTOR - Google Patents
GAS TURBINE ENGINE COMPRESSOR ROTOR Download PDFInfo
- Publication number
- RU2010125468A RU2010125468A RU2010125468/06A RU2010125468A RU2010125468A RU 2010125468 A RU2010125468 A RU 2010125468A RU 2010125468/06 A RU2010125468/06 A RU 2010125468/06A RU 2010125468 A RU2010125468 A RU 2010125468A RU 2010125468 A RU2010125468 A RU 2010125468A
- Authority
- RU
- Russia
- Prior art keywords
- compressor rotor
- windows
- sampling
- gas turbine
- turbine engine
- Prior art date
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- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
1. Ротор компрессора газотурбинного двигателя с рабочими колесами и с системой отбора охлаждающего воздуха внутри ротора, состоящей из трубок отбора для направления охлаждающего воздуха в турбину и с окнами для отбора воздуха, а также с болтовым соединением переднего и заднего рабочих колес, отличающийся тем, что окна для отбора воздуха выполнены на фланце заднего колеса между болтами с выходом их в проточную часть, при этом окна выполнены со скосом по вращению ротора. ! 2. Ротор компрессора по п.1, отличающийся тем, что перед поршневыми кольцами, установленными перед полостью отбора, расположенной под трубками отбора, выполнены упругие выступы. !3. Ротор компрессора по п.1, отличающийся тем, что нижний выступ переднего колеса имеет торцевой упор с задним колесом. 1. The compressor rotor of a gas turbine engine with impellers and with a cooling air extraction system inside the rotor, consisting of sampling tubes for directing cooling air to the turbine and with windows for air extraction, as well as with bolted connection of the front and rear impellers, characterized in that the windows for air sampling are made on the rear wheel flange between the bolts with their exit to the flow part, while the windows are beveled along the rotor rotation. ! 2. The compressor rotor according to claim 1, characterized in that in front of the piston rings installed in front of the sampling cavity located under the sampling tubes, elastic protrusions are made. ! 3. The compressor rotor according to claim 1, characterized in that the lower protrusion of the front wheel has an end stop with a rear wheel.
Claims (3)
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
RU2010125468/06A RU2451840C2 (en) | 2010-06-21 | 2010-06-21 | Compressor rotor of gas-turbine engine |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
RU2010125468/06A RU2451840C2 (en) | 2010-06-21 | 2010-06-21 | Compressor rotor of gas-turbine engine |
Publications (2)
Publication Number | Publication Date |
---|---|
RU2010125468A true RU2010125468A (en) | 2011-12-27 |
RU2451840C2 RU2451840C2 (en) | 2012-05-27 |
Family
ID=45782261
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
RU2010125468/06A RU2451840C2 (en) | 2010-06-21 | 2010-06-21 | Compressor rotor of gas-turbine engine |
Country Status (1)
Country | Link |
---|---|
RU (1) | RU2451840C2 (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN114651132A (en) * | 2019-09-05 | 2022-06-21 | 联合发动机制造集团股份公司 | Bleed air device in a turbojet compressor rotor |
Families Citing this family (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN103867235B (en) * | 2012-12-18 | 2015-12-23 | 中航商用航空发动机有限责任公司 | A kind of tubular type subtracts whirlpool device bleed air system |
RU2534680C1 (en) * | 2013-11-25 | 2014-12-10 | Российская Федерация, от имени которой выступает Министерство промышленности и торговли Российской Федерации (Минпромторг России) | Turbomachine rotor |
RU189794U1 (en) * | 2017-08-29 | 2019-06-04 | Акционерное общество "Объединенная двигателестроительная корпорация" (АО "ОДК") | ROTOR COMPRESSOR GAS TURBINE ENGINE |
Family Cites Families (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5271711A (en) * | 1992-05-11 | 1993-12-21 | General Electric Company | Compressor bore cooling manifold |
RU2036333C1 (en) * | 1992-09-24 | 1995-05-27 | Акционерное общество открытого типа "Авиадвигатель" | Stator for axial compressor of gas-turbine engine |
FR2834758B1 (en) * | 2002-01-17 | 2004-04-02 | Snecma Moteurs | DEVICE FOR STRAIGHTENING THE SUPPLY AIR OF A CENTRIPETE SAMPLING IN A COMPRESSOR |
DE10310815A1 (en) * | 2003-03-12 | 2004-09-23 | Rolls-Royce Deutschland Ltd & Co Kg | Vortex rectifier in tubular design with retaining ring |
RU2386864C1 (en) * | 2008-10-27 | 2010-04-20 | Открытое акционерное общество "Авиадвигатель" | Gas turbine engine compressor rotor |
-
2010
- 2010-06-21 RU RU2010125468/06A patent/RU2451840C2/en not_active IP Right Cessation
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN114651132A (en) * | 2019-09-05 | 2022-06-21 | 联合发动机制造集团股份公司 | Bleed air device in a turbojet compressor rotor |
Also Published As
Publication number | Publication date |
---|---|
RU2451840C2 (en) | 2012-05-27 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
MM4A | The patent is invalid due to non-payment of fees |
Effective date: 20140622 |