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RU2006124303A - GAS TURBINE COOLING SYSTEM OF A TURBOREACTIVE TWO-CIRCUIT ENGINE WITH ADDITIONAL COMPRESSION OF AIR IN A SMALL-SIZED FAN - Google Patents

GAS TURBINE COOLING SYSTEM OF A TURBOREACTIVE TWO-CIRCUIT ENGINE WITH ADDITIONAL COMPRESSION OF AIR IN A SMALL-SIZED FAN Download PDF

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Publication number
RU2006124303A
RU2006124303A RU2006124303/06A RU2006124303A RU2006124303A RU 2006124303 A RU2006124303 A RU 2006124303A RU 2006124303/06 A RU2006124303/06 A RU 2006124303/06A RU 2006124303 A RU2006124303 A RU 2006124303A RU 2006124303 A RU2006124303 A RU 2006124303A
Authority
RU
Russia
Prior art keywords
air
cooling system
small
gas turbine
turboreactive
Prior art date
Application number
RU2006124303/06A
Other languages
Russian (ru)
Other versions
RU2323359C1 (en
Inventor
Юрий Андреевич Караваев (RU)
Юрий Андреевич Караваев
Павел Геннадьевич Татарников (RU)
Павел Геннадьевич Татарников
Original Assignee
Иркутское высшее военное авиационное инженерное училище (военный институт) (RU)
Иркутское высшее военное авиационное инженерное училище (военный институт)
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 Иркутское высшее военное авиационное инженерное училище (военный институт) (RU), Иркутское высшее военное авиационное инженерное училище (военный институт) filed Critical Иркутское высшее военное авиационное инженерное училище (военный институт) (RU)
Priority to RU2006124303/06A priority Critical patent/RU2323359C1/en
Publication of RU2006124303A publication Critical patent/RU2006124303A/en
Application granted granted Critical
Publication of RU2323359C1 publication Critical patent/RU2323359C1/en

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

Claims (1)

Система охлаждения газовой турбины турбореактивного двухконтурного двигателя с дополнительным сжатием воздуха в малогабаритном вентиляторе, содержащая полость отбора вторичного потока воздуха из основной камеры сгорания, силовую диафрагму, комплект лопаток соплового аппарата, дефлекторы дисков, отличающаяся тем, что входные сечения центральных каналов лопаток соплового аппарата соединены посредством воздушного коллектора с козырьками забора воздуха из наружного контура, а выходные сечения этих каналов - с полостью подвода воздуха к центробежному вентилятору, установленному на валу турбины высокого давления.A gas turbine cooling system for a turbojet bypass engine with additional air compression in a small-sized fan, containing a secondary air flow sampling cavity from the main combustion chamber, a power diaphragm, a set of nozzle vanes, disk deflectors, characterized in that the input sections of the central channels of the nozzle vanes are connected by air manifold with visors for air intake from the external circuit, and the output sections of these channels with the air supply cavity to a centrifugal fan mounted on the shaft of the high pressure turbine.
RU2006124303/06A 2006-07-06 2006-07-06 Cooling system of gas turbine of double-flow turbojet engine with additional compression of air ion small-size fan RU2323359C1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
RU2006124303/06A RU2323359C1 (en) 2006-07-06 2006-07-06 Cooling system of gas turbine of double-flow turbojet engine with additional compression of air ion small-size fan

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
RU2006124303/06A RU2323359C1 (en) 2006-07-06 2006-07-06 Cooling system of gas turbine of double-flow turbojet engine with additional compression of air ion small-size fan

Publications (2)

Publication Number Publication Date
RU2006124303A true RU2006124303A (en) 2008-01-20
RU2323359C1 RU2323359C1 (en) 2008-04-27

Family

ID=39108198

Family Applications (1)

Application Number Title Priority Date Filing Date
RU2006124303/06A RU2323359C1 (en) 2006-07-06 2006-07-06 Cooling system of gas turbine of double-flow turbojet engine with additional compression of air ion small-size fan

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RU (1) RU2323359C1 (en)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2939470B1 (en) * 2008-12-10 2011-01-07 Snecma BLOWER FOR TURBOMACHINE COMPRISING A BALANCING SYSTEM HAVING MOUNTED HOUSING HOUSES
RU2499145C1 (en) * 2012-05-21 2013-11-20 Николай Борисович Болотин Turbine of bypass gas turbine engine
RU2501956C1 (en) * 2012-07-31 2013-12-20 Николай Борисович Болотин Bypass gas turbine engine, method of radial gap adjustment in turbine of bypass gas turbine engine
RU2641787C2 (en) * 2016-05-30 2018-01-22 Общество с ограниченной ответственностью "Газпром трансгаз Казань" Gas-driven turbines high-temperature stud pins refrigeration method and device for its actualization

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1502738A (en) * 1966-07-28 1967-11-24 Snecma Cooling method and device applicable in particular to turbine blades
US3575528A (en) * 1968-10-28 1971-04-20 Gen Motors Corp Turbine rotor cooling
SU1064695A1 (en) * 1979-09-26 1996-10-20 В.Н. Орлов Gas turbine power plant
SU1542156A1 (en) * 1987-02-12 1995-01-09 Уфимский авиационный институт им.Серго Орджоникидзе Method of operation of gas turbine engine

Also Published As

Publication number Publication date
RU2323359C1 (en) 2008-04-27

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

Effective date: 20080707