RU2008121291A - ATOMIC GAS-TURBINE AIRCRAFT ENGINE - Google Patents
ATOMIC GAS-TURBINE AIRCRAFT ENGINE Download PDFInfo
- Publication number
- RU2008121291A RU2008121291A RU2008121291/06A RU2008121291A RU2008121291A RU 2008121291 A RU2008121291 A RU 2008121291A RU 2008121291/06 A RU2008121291/06 A RU 2008121291/06A RU 2008121291 A RU2008121291 A RU 2008121291A RU 2008121291 A RU2008121291 A RU 2008121291A
- Authority
- RU
- Russia
- Prior art keywords
- turbine
- aircraft engine
- atomic gas
- stages
- combustion chamber
- Prior art date
Links
- 238000002485 combustion reaction Methods 0.000 claims abstract 4
- 239000002826 coolant Substances 0.000 claims abstract 2
Landscapes
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
1. Атомный газотурбинный авиационный двигатель, содержащий внутренний и второй контуры, внешний и внутренний валы с вентилятором, установленным на внутреннем валу, и компрессор, установленный на внешнем валу, а также две ступени турбины, каждая из которых имеет, по меньшей мере, одно рабочее колесо турбины, установленное соответственно на внешнем и внутреннем валах, камеру сгорания между компрессором и первой ступенью турбины, и теплообменник, установленный перед камерой сгорания, реактивное сопло, отличающийся тем, что между ступенями турбины установлены теплообменники, соединенные трубопроводами циркуляции теплоносителя с ядерным реактором. ! 2. Атомный газотурбинный авиационный двигатель по п.1, отличающийся тем, что во втором контуре установлен теплообменник, соединенный трубопроводами рециркуляции с ядерным реактором.1. Atomic gas turbine aircraft engine containing the inner and second circuits, the outer and inner shafts with a fan mounted on the inner shaft, and a compressor mounted on the outer shaft, as well as two stages of the turbine, each of which has at least one working a turbine wheel mounted respectively on the external and internal shafts, a combustion chamber between the compressor and the first stage of the turbine, and a heat exchanger installed in front of the combustion chamber, a jet nozzle, characterized in that between the stages There are installed heat exchangers connected by coolant circulation pipelines to a nuclear reactor. ! 2. The atomic gas turbine aircraft engine according to claim 1, characterized in that in the second circuit there is a heat exchanger connected by recirculation pipelines to a nuclear reactor.
Claims (2)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| RU2008121291/06A RU2008121291A (en) | 2008-05-27 | 2008-05-27 | ATOMIC GAS-TURBINE AIRCRAFT ENGINE |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| RU2008121291/06A RU2008121291A (en) | 2008-05-27 | 2008-05-27 | ATOMIC GAS-TURBINE AIRCRAFT ENGINE |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| RU2008121291A true RU2008121291A (en) | 2009-12-27 |
Family
ID=41642212
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| RU2008121291/06A RU2008121291A (en) | 2008-05-27 | 2008-05-27 | ATOMIC GAS-TURBINE AIRCRAFT ENGINE |
Country Status (1)
| Country | Link |
|---|---|
| RU (1) | RU2008121291A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111447696A (en) * | 2020-04-03 | 2020-07-24 | 中国航空工业集团公司北京长城计量测试技术研究所 | Atomic air chamber heating device |
-
2008
- 2008-05-27 RU RU2008121291/06A patent/RU2008121291A/en unknown
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111447696A (en) * | 2020-04-03 | 2020-07-24 | 中国航空工业集团公司北京长城计量测试技术研究所 | Atomic air chamber heating device |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| Aydin | Exergetic sustainability analysis of LM6000 gas turbine power plant with steam cycle | |
| US9797310B2 (en) | Heat pipe temperature management system for a turbomachine | |
| JP6739956B2 (en) | Turbine engine with integrated heat recovery and cooling cycle system | |
| JP2012246927A5 (en) | ||
| US20160290235A1 (en) | Heat pipe temperature management system for a turbomachine | |
| JP6431690B2 (en) | Turbine rotor blade for the turbine section of a gas turbine | |
| CA2777977A1 (en) | Flade duct turbine cooling and power and thermal management | |
| JP2013527357A5 (en) | ||
| JP2012246928A5 (en) | ||
| US9341119B2 (en) | Cooling air system for aircraft turbine engine | |
| US11519294B2 (en) | Aircraft propulsion system with vapor absorption refrigeration system | |
| WO2018143310A1 (en) | Hydrogen/oxygen equivalent combustion turbine system | |
| JP2013139784A (en) | Method and apparatus for operating gas turbine engine | |
| JP2010038536A (en) | Heat recovery system for turbomachine, and method of operating heat recovery steam system for turbomachine | |
| CN202144751U (en) | Gas and steam turbine system | |
| JP2013148082A (en) | Gas turbine device | |
| CN103016114A (en) | Exhaust waste heat power system of internal-combustion engine | |
| JP5099967B2 (en) | Method and apparatus for operating a gas turbine engine | |
| RU2008121291A (en) | ATOMIC GAS-TURBINE AIRCRAFT ENGINE | |
| CN202250397U (en) | Gas and steam turbine system | |
| RU2012140749A (en) | VERTICAL SHAFT TURBOCHARGER | |
| RU2008122636A (en) | NUCLEAR GAS-TURBINE AIRCRAFT ENGINE WITH COOLED TURBINE | |
| RU2008122637A (en) | ATOMIC GAS-TURBINE ENGINE | |
| RU2007101145A (en) | GAS-TURBINE POWER PLANT | |
| RU2008138792A (en) | COMBINED ATOMIC FORCING AIRCRAFT ENGINE |