SU1633892A1 - FUEL SUPPLY SYSTEM IN THE FORCESSIONAL COMBUSTION CHAMBER OF A TWO-CIRCUIT GAS TURBINE ENGINE - Google Patents

FUEL SUPPLY SYSTEM IN THE FORCESSIONAL COMBUSTION CHAMBER OF A TWO-CIRCUIT GAS TURBINE ENGINE

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Publication number
SU1633892A1
SU1633892A1 SU4645141/06A SU4645141A SU1633892A1 SU 1633892 A1 SU1633892 A1 SU 1633892A1 SU 4645141/06 A SU4645141/06 A SU 4645141/06A SU 4645141 A SU4645141 A SU 4645141A SU 1633892 A1 SU1633892 A1 SU 1633892A1
Authority
SU
USSR - Soviet Union
Prior art keywords
combustion chamber
fuel supply
turbine engine
supply system
fuel
Prior art date
Application number
SU4645141/06A
Other languages
Russian (ru)
Inventor
А.Д. Росляков
Н.И. Левичев
Б.Г. Розно
В.А. Кудинов
А.В. Кузьмичев
Original Assignee
А.Д. Росляков
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 А.Д. Росляков filed Critical А.Д. Росляков
Priority to SU4645141/06A priority Critical patent/SU1633892A1/en
Application granted granted Critical
Publication of SU1633892A1 publication Critical patent/SU1633892A1/en

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  • Fluidized-Bed Combustion And Resonant Combustion (AREA)

Abstract

Система подачи топлива в форсажную камеру сгорания двухконтурного газотурбинного двигателя, содержащая топливные коллекторы и подключенный к ним трубопровод подвода топлива с радиальным участком, расположенным в зонах наружного контура и за смесителем, отличающаяся тем, что, с целью уменьшения закоксовывания топливных трактов при температуре газа на входе в камеру сгорания в зоне внутреннего контура, превышающей значение 650°C, система снабжена трубкой, имеющей на внутренней поверхности эмалированное покрытие и установленной в трубопроводе на его радиальном участке, а участок трубопровода, расположенный по потоку топлива за трубкой, размещен в зоне внутреннего контура.Fuel supply system to the afterburner combustion chamber of a double-circuit gas-turbine engine containing fuel manifolds and a fuel supply pipe connected to them with a radial section located in the outer contour zones and behind the mixer, characterized in that in order to reduce the coking of fuel paths at the inlet gas temperature in the combustion chamber in the zone of the internal circuit, exceeding the value of 650 ° C, the system is equipped with a tube that has an enamelled coating on the inner surface and is installed in the pipe Gadfly on its radial portion, and the portion of the duct disposed downstream of the fuel tube, located in the inner loop area.

SU4645141/06A 1988-12-26 1988-12-26 FUEL SUPPLY SYSTEM IN THE FORCESSIONAL COMBUSTION CHAMBER OF A TWO-CIRCUIT GAS TURBINE ENGINE SU1633892A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
SU4645141/06A SU1633892A1 (en) 1988-12-26 1988-12-26 FUEL SUPPLY SYSTEM IN THE FORCESSIONAL COMBUSTION CHAMBER OF A TWO-CIRCUIT GAS TURBINE ENGINE

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
SU4645141/06A SU1633892A1 (en) 1988-12-26 1988-12-26 FUEL SUPPLY SYSTEM IN THE FORCESSIONAL COMBUSTION CHAMBER OF A TWO-CIRCUIT GAS TURBINE ENGINE

Publications (1)

Publication Number Publication Date
SU1633892A1 true SU1633892A1 (en) 2004-07-10

Family

ID=60520013

Family Applications (1)

Application Number Title Priority Date Filing Date
SU4645141/06A SU1633892A1 (en) 1988-12-26 1988-12-26 FUEL SUPPLY SYSTEM IN THE FORCESSIONAL COMBUSTION CHAMBER OF A TWO-CIRCUIT GAS TURBINE ENGINE

Country Status (1)

Country Link
SU (1) SU1633892A1 (en)

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