RU2005113851A - TUBULAR-RING COMBUSTION CAMERA OF A GAS-TURBINE ENGINE - Google Patents

TUBULAR-RING COMBUSTION CAMERA OF A GAS-TURBINE ENGINE Download PDF

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Publication number
RU2005113851A
RU2005113851A RU2005113851/06A RU2005113851A RU2005113851A RU 2005113851 A RU2005113851 A RU 2005113851A RU 2005113851/06 A RU2005113851/06 A RU 2005113851/06A RU 2005113851 A RU2005113851 A RU 2005113851A RU 2005113851 A RU2005113851 A RU 2005113851A
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RU
Russia
Prior art keywords
head
flame tube
deflector
gas
cavity
Prior art date
Application number
RU2005113851/06A
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Russian (ru)
Other versions
RU2300706C2 (en
Inventor
щиков Михаил Сергеевич Хр (RU)
Михаил Сергеевич Хрящиков
Валерий Алексеевич Кузнецов (RU)
Валерий Алексеевич Кузнецов
Original Assignee
Открытое акционерное общество "Авиадвигатель" (RU)
Открытое акционерное общество "Авиадвигатель"
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Application filed by Открытое акционерное общество "Авиадвигатель" (RU), Открытое акционерное общество "Авиадвигатель" filed Critical Открытое акционерное общество "Авиадвигатель" (RU)
Priority to RU2005113851/06A priority Critical patent/RU2300706C2/en
Publication of RU2005113851A publication Critical patent/RU2005113851A/en
Application granted granted Critical
Publication of RU2300706C2 publication Critical patent/RU2300706C2/en

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Claims (1)

Трубчато-кольцевая камера сгорания газотурбинного двигателя, в головке которой со стороны газовой полости жаровой трубы установлены дефлектор, образующий кольцевую воздушную полость с головкой, а также воздушный двухъярусный завихритель с внешней стороны жаровой трубы, причем с жестким креплением между собой заклепочным соединением головки жаровой трубы, завихрителя и дефлектора, отличающаяся тем, что дефлектор относительно головки жаровой трубы установлен телескопически с помощью осевых стержней, выполненных за одно целое с дефлектором и проходящих с зазором через отверстия в головке жаровой трубы, а также зафиксирован в осевом направлении втулками, установленными на стержнях с внешней стороны жаровой трубы, контактирующими боковыми поверхностями с ответными выемками в завихрителе и примыкающими одним торцом к головке жаровой трубы, а другим - к головке стержня, при этом дефлектор дополнительно установлен внутренними осевыми выступами на внешнем радиальном кольцевом ребре завихрителя, а воздушная полость между головкой жаровой трубы и дефлектором выполнена сообщающейся с охлаждающим воздухом через перфорацию в головке жаровой трубы и соединена на выходе с газовой полостью жаровой трубы через щелевые кольцевые полости.A tube-annular combustion chamber of a gas turbine engine, in the head of which, on the side of the gas cavity of the flame tube, a deflector is installed that forms an annular air cavity with a head, as well as an air two-tier swirler on the outside of the flame tube, and with a riveted connection between the head of the flame tube swirl and deflector, characterized in that the deflector relative to the head of the flame tube is mounted telescopically using axial rods made in one piece with the deflector torus and passing with a gap through the holes in the head of the flame tube, and also axially fixed by bushings mounted on rods on the outside of the flame tube, contacting side surfaces with reciprocal recesses in the swirler and adjacent one end to the head of the flame tube, and the other to the head of the rod, while the deflector is additionally mounted with internal axial protrusions on the outer radial annular rib of the swirl, and the air cavity between the head of the flame tube and the deflector is made with bschayuscheysya with the cooling air through the perforation in the head of the flame tube and is connected at the outlet with a gas cavity of the flame tube through the annular gap cavity.
RU2005113851/06A 2005-05-05 2005-05-05 Tubular annular combustion chamber of gas-turbine engine RU2300706C2 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
RU2005113851/06A RU2300706C2 (en) 2005-05-05 2005-05-05 Tubular annular combustion chamber of gas-turbine engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
RU2005113851/06A RU2300706C2 (en) 2005-05-05 2005-05-05 Tubular annular combustion chamber of gas-turbine engine

Publications (2)

Publication Number Publication Date
RU2005113851A true RU2005113851A (en) 2006-11-20
RU2300706C2 RU2300706C2 (en) 2007-06-10

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ID=37501624

Family Applications (1)

Application Number Title Priority Date Filing Date
RU2005113851/06A RU2300706C2 (en) 2005-05-05 2005-05-05 Tubular annular combustion chamber of gas-turbine engine

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RU (1) RU2300706C2 (en)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
PL2201299T3 (en) * 2007-10-26 2011-10-31 Siemens Ag Support ring for heat shield elements on a flame tube and a combustion chamber arrangement with said support ring
FR2955374B1 (en) * 2010-01-15 2012-05-18 Turbomeca MULTI-PERCEED COMBUSTION CHAMBER WITH TANGENTIAL DISCHARGES AGAINST GIRATORY

Also Published As

Publication number Publication date
RU2300706C2 (en) 2007-06-10

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Effective date: 20170506