RU2006130936A - GAS TURBINE ENGINE - Google Patents

GAS TURBINE ENGINE Download PDF

Info

Publication number
RU2006130936A
RU2006130936A RU2006130936/06A RU2006130936A RU2006130936A RU 2006130936 A RU2006130936 A RU 2006130936A RU 2006130936/06 A RU2006130936/06 A RU 2006130936/06A RU 2006130936 A RU2006130936 A RU 2006130936A RU 2006130936 A RU2006130936 A RU 2006130936A
Authority
RU
Russia
Prior art keywords
gas turbine
turbine engine
housing
compressor
combustion chamber
Prior art date
Application number
RU2006130936/06A
Other languages
Russian (ru)
Other versions
RU2330167C2 (en
Inventor
Анатолий Иванович Тункин (RU)
Анатолий Иванович Тункин
Original Assignee
Открытое акционерное общество "Авиадвигатель" (RU)
Открытое акционерное общество "Авиадвигатель"
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Открытое акционерное общество "Авиадвигатель" (RU), Открытое акционерное общество "Авиадвигатель" filed Critical Открытое акционерное общество "Авиадвигатель" (RU)
Priority to RU2006130936/06A priority Critical patent/RU2330167C2/en
Publication of RU2006130936A publication Critical patent/RU2006130936A/en
Application granted granted Critical
Publication of RU2330167C2 publication Critical patent/RU2330167C2/en

Links

Landscapes

  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (2)

1. Газотурбинный двигатель, содержащий наружный силовой и внутренний корпуса компрессора высокого давления, корпус стоек камеры сгорания, отличающийся тем, что внутренний корпус компрессора соединен с наружным силовым корпусом компрессора и с корпусом стоек камеры сгорания двумя упругими обечайками.1. A gas turbine engine comprising an outer power and inner housing of a high pressure compressor, a housing of the struts of the combustion chamber, characterized in that the inner housing of the compressor is connected to the outer power housing of the compressor and with the housing of the struts of the combustion chamber by two elastic shells. 2. Газотурбинный двигатель по п.1, отличающийся тем, что корпус стоек камеры сгорания соединен с наружным силовым корпусом и с внутренним корпусом компрессора двумя упругими обечайками.2. The gas turbine engine according to claim 1, characterized in that the housing of the racks of the combustion chamber is connected to the outer power housing and to the inner housing of the compressor by two elastic shells.
RU2006130936/06A 2006-08-28 2006-08-28 Gas turbine engine RU2330167C2 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
RU2006130936/06A RU2330167C2 (en) 2006-08-28 2006-08-28 Gas turbine engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
RU2006130936/06A RU2330167C2 (en) 2006-08-28 2006-08-28 Gas turbine engine

Publications (2)

Publication Number Publication Date
RU2006130936A true RU2006130936A (en) 2008-03-10
RU2330167C2 RU2330167C2 (en) 2008-07-27

Family

ID=39280358

Family Applications (1)

Application Number Title Priority Date Filing Date
RU2006130936/06A RU2330167C2 (en) 2006-08-28 2006-08-28 Gas turbine engine

Country Status (1)

Country Link
RU (1) RU2330167C2 (en)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2463465C1 (en) * 2011-04-29 2012-10-10 Открытое акционерное общество "Авиадвигатель" Gas turbine engine

Also Published As

Publication number Publication date
RU2330167C2 (en) 2008-07-27

Similar Documents

Publication Publication Date Title
EP2011962A3 (en) Compound cycle rotary engine
EA200701014A1 (en) IMPROVING THE POWER OF TURBINES OF INTERNAL COMBUSTION BY MEANS OF ACCUMULATING ENERGY OF COMPRESSED AIR AND ADDITIONAL DETANDER, WITH AIR FLOW REMOVAL AND ITS INLET ABOVE THE FLOW OF THE BURNING CHAMBER
CO6141487A2 (en) FILTER FOR DIESEL IMPACT PARTICLES
ATE510108T1 (en) TRANSITION PIECE OF A GAS TURBINE COMBUSTION CHAMBER
EA200301220A1 (en) ROTOR MACHINE AND THERMODYNAMIC CYCLE
RU2014119916A (en) GAS-TURBINE ENGINE COMPRESSOR DESIGN
JP2012207565A5 (en)
RU2008100463A (en) TURBO-FAN ENGINE
WO2011084283A3 (en) Turbocharger
EA201190075A1 (en) TURBOCHARGER WITH EXHAUST EXTERNAL TUBE AND ENHANCED TRANSVERSE SECTION AND METHOD OF TURBO SURGERY
RU2005108494A (en) GAS-TURBINE ENGINE CONTAINING TWO UNITS UNITED UNDER AXIAL FORCE
RU2006130936A (en) GAS TURBINE ENGINE
FR2891351B1 (en) GAS TURBINE ENGINE COMBUSTION CHAMBER WITH CARENAGE
RU2007143809A (en) TRIGENERAL GAS-TURBINE INSTALLATION
CA2523967A1 (en) Device for injecting water or water vapor into the working medium of a gas turbine plant
RU2007116761A (en) ROTARY ENGINE
RU2008101875A (en) GAS-TURBINE AIR INSTALLATION
RU2009121483A (en) STEAM ENGINE
RU2010125476A (en) GAS TURBINE ENGINE COMPRESSOR STATOR
RU2006128976A (en) STEAM GAS INSTALLATION
RU2012113194A (en) METHOD FOR INCREASING POWER AND KPD GAS TURBINE ENGINE
RU2007147567A (en) FAN AIRCRAFT ENGINE
RU2002130401A (en) GAS TURBINE ENGINE
WO2008104569A3 (en) Oscillating piston-type internal combustion engine
RU2008102861A (en) SOUND MUFFLER SHOT

Legal Events

Date Code Title Description
MM4A The patent is invalid due to non-payment of fees

Effective date: 20100829