RU2010152140A - COMPRESSOR TURBINE AIRCRAFT ENGINE - Google Patents
COMPRESSOR TURBINE AIRCRAFT ENGINE Download PDFInfo
- Publication number
- RU2010152140A RU2010152140A RU2010152140/06A RU2010152140A RU2010152140A RU 2010152140 A RU2010152140 A RU 2010152140A RU 2010152140/06 A RU2010152140/06 A RU 2010152140/06A RU 2010152140 A RU2010152140 A RU 2010152140A RU 2010152140 A RU2010152140 A RU 2010152140A
- Authority
- RU
- Russia
- Prior art keywords
- compressor
- aircraft engine
- turbine
- engine according
- turbine aircraft
- Prior art date
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Abstract
1. Компрессорно-турбинный авиационный двигатель, содержащий входное устройство, камеру сгорания, турбину, форсажную камеру и выходное устройство, отличающийся тем, что газовая турбина расположена сразу за компрессором. ! 2. Компрессорно-турбинный авиационный двигатель по п.1, отличающийся тем, что патрубки выходного устройства расположены между компрессором и турбиной, и смещены от оси двигателя, обеспечивая создание дополнительных осевых сил, увеличивающих тягу авиационного двигателя. ! 3. Компрессорно-турбинный авиационный двигатель по п.1, отличающийся тем, что камера сгорания располагается за газовой турбиной по обратной схеме, обеспечивая создание дополнительных осевых сил, увеличивающих тягу авиационного двигателя. ! 4. Компрессорно-турбинный авиационный двигатель по п.1, отличающийся тем, что авиационный двигатель имеет меньшую массу за счет уменьшения количества валов и длины вала. ! 5. Компрессорно-турбинный авиационный двигатель по п.1, отличающийся тем, что эффективное использование компрессора делает нецелесообразным вторичный контур. 1. Compressor-turbine aircraft engine containing an input device, a combustion chamber, a turbine, an afterburner and an output device, characterized in that the gas turbine is located immediately after the compressor. ! 2. The compressor-turbine aircraft engine according to claim 1, characterized in that the nozzles of the output device are located between the compressor and the turbine and are offset from the axis of the engine, providing the creation of additional axial forces that increase the thrust of the aircraft engine. ! 3. The compressor-turbine aircraft engine according to claim 1, characterized in that the combustion chamber is located behind the gas turbine in the reverse way, ensuring the creation of additional axial forces that increase the thrust of the aircraft engine. ! 4. The compressor-turbine aircraft engine according to claim 1, characterized in that the aircraft engine has a lower mass by reducing the number of shafts and shaft length. ! 5. The compressor-turbine aircraft engine according to claim 1, characterized in that the effective use of the compressor makes the secondary circuit inappropriate.
Claims (5)
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
RU2010152140/06A RU2010152140A (en) | 2010-12-20 | 2010-12-20 | COMPRESSOR TURBINE AIRCRAFT ENGINE |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
RU2010152140/06A RU2010152140A (en) | 2010-12-20 | 2010-12-20 | COMPRESSOR TURBINE AIRCRAFT ENGINE |
Publications (1)
Publication Number | Publication Date |
---|---|
RU2010152140A true RU2010152140A (en) | 2012-06-27 |
Family
ID=46681547
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
RU2010152140/06A RU2010152140A (en) | 2010-12-20 | 2010-12-20 | COMPRESSOR TURBINE AIRCRAFT ENGINE |
Country Status (1)
Country | Link |
---|---|
RU (1) | RU2010152140A (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
RU2703888C2 (en) * | 2014-10-09 | 2019-10-22 | Сафран Аэро Бустерс Са | Compressor of axial gas-turbine engine with rotor of opposite rotation |
-
2010
- 2010-12-20 RU RU2010152140/06A patent/RU2010152140A/en not_active Application Discontinuation
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
RU2703888C2 (en) * | 2014-10-09 | 2019-10-22 | Сафран Аэро Бустерс Са | Compressor of axial gas-turbine engine with rotor of opposite rotation |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
FA92 | Acknowledgement of application withdrawn (lack of supplementary materials submitted) |
Effective date: 20121116 |