RU2009107639A - TURBOJET - Google Patents
TURBOJET Download PDFInfo
- Publication number
- RU2009107639A RU2009107639A RU2009107639/06A RU2009107639A RU2009107639A RU 2009107639 A RU2009107639 A RU 2009107639A RU 2009107639/06 A RU2009107639/06 A RU 2009107639/06A RU 2009107639 A RU2009107639 A RU 2009107639A RU 2009107639 A RU2009107639 A RU 2009107639A
- Authority
- RU
- Russia
- Prior art keywords
- combustion chamber
- gas
- compressor
- turbine
- temperature combustion
- Prior art date
Links
- 238000002485 combustion reaction Methods 0.000 claims abstract 8
Landscapes
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
1. Турбореактивный двигатель, содержащий входное устройство, компрессор, основную камеру сгорания, газовую турбину для привода компрессора, дополнительную высокотемпературную камеру сгорания с отбором воздуха в нее из компрессора, реактивное сопло, расположенное за высокотемпературной камерой сгорания, отличающийся тем, что канал для выхода газа из турбины в атмосферу выполнен с постоянной, а также с увеличивающейся к выходу площадью проходного сечения. ! 2. Турбореактивный двигатель по п.1, отличающийся тем, что выходное отверстие канала для выхода газа из турбины в атмосферу расположено в зоне пониженного давления, образованного течением воздуха, обтекающим мотогандолу, а также реактивной струей газа, выходящего из реактивного сопла, расположенного за высокотемпературной камерой сгорания. 1. A turbojet engine containing an input device, a compressor, a main combustion chamber, a gas turbine for driving a compressor, an additional high-temperature combustion chamber with air taken into it from the compressor, a jet nozzle located behind the high-temperature combustion chamber, characterized in that the gas outlet from the turbine to the atmosphere it is made with a constant, as well as with a passage area increasing towards the exit. ! 2. The turbojet engine according to claim 1, characterized in that the outlet of the channel for the exit of gas from the turbine into the atmosphere is located in the zone of reduced pressure formed by the flow of air flowing around the motogandola, as well as a jet of gas leaving the jet nozzle located behind the high-temperature combustion chamber.
Claims (2)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| RU2009107639/06A RU2418969C2 (en) | 2009-03-03 | 2009-03-03 | Turbojet engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| RU2009107639/06A RU2418969C2 (en) | 2009-03-03 | 2009-03-03 | Turbojet engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| RU2009107639A true RU2009107639A (en) | 2010-09-10 |
| RU2418969C2 RU2418969C2 (en) | 2011-05-20 |
Family
ID=42800127
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| RU2009107639/06A RU2418969C2 (en) | 2009-03-03 | 2009-03-03 | Turbojet engine |
Country Status (1)
| Country | Link |
|---|---|
| RU (1) | RU2418969C2 (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2980266B1 (en) * | 2011-09-15 | 2014-06-13 | Snecma | MONITORING SYSTEM OF A MEASUREMENT CHAIN OF A TURBOJETACTOR |
| RU2491439C1 (en) * | 2012-03-11 | 2013-08-27 | Георгий Галиуллович Валеев | Turbojet protected against self-guided rocket and method of its protection (versions) |
| RU2727532C1 (en) * | 2019-11-29 | 2020-07-22 | Владимир Дмитриевич Куликов | Turbojet engine |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2930190A (en) * | 1958-04-29 | 1960-03-29 | Westinghouse Electric Corp | Bypass gas turbine power plant employing regenerative cycle |
| US3938328A (en) * | 1971-11-08 | 1976-02-17 | The Boeing Company | Multicycle engine |
| US4163366A (en) * | 1977-05-23 | 1979-08-07 | Avco Corporation | Apparatus for disposal of leaking fluids in a turbofan engine |
| DE3644610A1 (en) * | 1986-12-29 | 1987-10-08 | Weber Franz Josef | Gas-turbine jet engine |
| SU1747730A1 (en) * | 1989-04-14 | 1992-07-15 | Казанский Авиационный Институт Им.А.Н.Туполева | Method and device for operation of hybrid air-jet engine |
-
2009
- 2009-03-03 RU RU2009107639/06A patent/RU2418969C2/en not_active IP Right Cessation
Also Published As
| Publication number | Publication date |
|---|---|
| RU2418969C2 (en) | 2011-05-20 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| GB2468669C (en) | A flow discharge device | |
| WO2009041436A1 (en) | Gas turbine combustor | |
| RU2013112153A (en) | TURBINE, GAS TURBINE ENGINE AND METHOD FOR COOLING THE FRAME OF THE EXHAUST TURBINE TUBE | |
| EP2017826A3 (en) | An acoustic panel | |
| EP2384400A4 (en) | Variable pressure ratio compressor | |
| GB201115043D0 (en) | Steam injected gas turbine engine | |
| RU2012158330A (en) | GAS-TURBINE ENGINE AND AIR DIRECTION METHOD | |
| MX2009004301A (en) | Venturi cooling system. | |
| WO2010014324A3 (en) | System and method of operating a gas turbine engine with an alternate working fluid | |
| WO2016126986A3 (en) | Systems and methods for high volumetric oxidant flow in gas turbine engine with exhaust gas recirculation | |
| RU2012111248A (en) | BURNER, IN PARTICULAR, FOR GAS TURBINES | |
| SA113340953B1 (en) | Combustor transition adapted to guide combustion gases in a hot gas flow path | |
| WO2013029984A3 (en) | Combustion chamber for a gas turbine plant | |
| RU2012115610A (en) | GAS TURBINE ENGINE | |
| RU2013121279A (en) | SECONDARY COMBUSTION DEVICE (OPTIONS) | |
| ATE523682T1 (en) | ARRANGEMENT FOR DRIVING AN AIRCRAFT, AIRCRAFT AND EXHAUST NOZZLE FOR A JET ENGINE | |
| RU2009107639A (en) | TURBOJET | |
| WO2011146096A3 (en) | Combustor system | |
| RU2013129579A (en) | COMBUSTION CAMERA INJECTOR, GAS TURBINE AND METHOD INCLUDING AIR AND FUEL MIXING | |
| WO2013096591A3 (en) | Can annular combustion arrangement with flow tripping device | |
| RU2011114830A (en) | DEVICE FOR SUPPLYING THE INTERNAL COMBUSTION ENGINE, CAR AND METHOD FOR SUPPLYING THE INTERNAL COMBUSTION ENGINE | |
| RU2012138960A (en) | GAS TURBINE ENGINE | |
| RU2013140422A (en) | TURBOMACHINE COMBUSTION INJECTION DEVICE | |
| RU2008108083A (en) | METHOD AND DEVICE FOR STARTING A GAS-TURBINE UNIT | |
| RU2011150673A (en) | TWO-CIRCUIT GAS-TURBINE ENGINE |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| MM4A | The patent is invalid due to non-payment of fees |
Effective date: 20120304 |