RU2008138790A - COMBINED AIRCRAFT ENGINE - Google Patents
COMBINED AIRCRAFT ENGINE Download PDFInfo
- Publication number
- RU2008138790A RU2008138790A RU2008138790/06A RU2008138790A RU2008138790A RU 2008138790 A RU2008138790 A RU 2008138790A RU 2008138790/06 A RU2008138790/06 A RU 2008138790/06A RU 2008138790 A RU2008138790 A RU 2008138790A RU 2008138790 A RU2008138790 A RU 2008138790A
- Authority
- RU
- Russia
- Prior art keywords
- turbine
- engine
- cylinder
- cavity
- expansion
- Prior art date
Links
- 238000001816 cooling Methods 0.000 claims abstract 6
- 239000000446 fuel Substances 0.000 claims abstract 4
- 238000002485 combustion reaction Methods 0.000 claims abstract 2
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
1. Комбинированный авиационный двигатель, содержащий двухкаскадный газотурбинный двигатель с внутренним и внешним валами и двумя каскадами компрессора, камерой сгорания, к которой подведен топливный трубопровод от топливного насоса, турбиной и реактивным соплом, отличающийся тем, что за турбиной на внутреннем валу двигателя установлен двигатель Стирлинга, который содержит, мо меньшей мере один рабочий цилиндр, установленный за турбиной по потоку, и по меньшей мере один расширительный цилиндр, установленный за рабочим цилиндром по потоку, при этом каждый расширительный цилиндр имеет кожух, образующий с этим цилиндром охлаждающую полость, вход в охлаждающую полость соединен с выходом воздухозаборного патрубка, вход которого соединен через регулятор расхода с полостью компрессора, выход из охлаждающей полости соединен с полостью внутри реактивного сопла. ! 2. Комбинированный авиационный двигатель по п.1, отличающийся тем, что все расширительные цилиндры частично или полностью установлены внутри обтекателя реактивного сопла. 1. Combined aircraft engine containing a two-stage gas turbine engine with internal and external shafts and two compressor stages, a combustion chamber to which the fuel pipe is connected from the fuel pump, a turbine and a jet nozzle, characterized in that a Stirling engine is installed behind the turbine on the internal shaft of the engine which contains at least one working cylinder mounted downstream of the turbine and at least one expansion cylinder installed downstream of the working cylinder y, wherein each expansion cylinder having a housing defining with the cylinder cooling cavity entrance into the cooling chamber connected to the outlet of the air intake manifold, the input of which is connected through a flow regulator to the cavity of the compressor, the output of the cooling chamber is connected with a cavity inside the nozzle. ! 2. The combined aircraft engine according to claim 1, characterized in that all the expansion cylinders are partially or completely installed inside the radome of the jet nozzle.
Claims (2)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| RU2008138790/06A RU2008138790A (en) | 2008-09-29 | 2008-09-29 | COMBINED AIRCRAFT ENGINE |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| RU2008138790/06A RU2008138790A (en) | 2008-09-29 | 2008-09-29 | COMBINED AIRCRAFT ENGINE |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| RU2008138790A true RU2008138790A (en) | 2010-04-10 |
Family
ID=42670834
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| RU2008138790/06A RU2008138790A (en) | 2008-09-29 | 2008-09-29 | COMBINED AIRCRAFT ENGINE |
Country Status (1)
| Country | Link |
|---|---|
| RU (1) | RU2008138790A (en) |
-
2008
- 2008-09-29 RU RU2008138790/06A patent/RU2008138790A/en not_active Application Discontinuation
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| FA92 | Acknowledgement of application withdrawn (lack of supplementary materials submitted) |
Effective date: 20100520 |