RU94028910A - Gas-turbine engine exhaust unit - Google Patents

Gas-turbine engine exhaust unit

Info

Publication number
RU94028910A
RU94028910A RU94028910/06A RU94028910A RU94028910A RU 94028910 A RU94028910 A RU 94028910A RU 94028910/06 A RU94028910/06 A RU 94028910/06A RU 94028910 A RU94028910 A RU 94028910A RU 94028910 A RU94028910 A RU 94028910A
Authority
RU
Russia
Prior art keywords
fairing
turbine engine
exhaust unit
gas
engine exhaust
Prior art date
Application number
RU94028910/06A
Other languages
Russian (ru)
Other versions
RU2096631C1 (en
Inventor
Ю.А. Долгополов
В.С. Хроменков
Original Assignee
Научно-производственное предприятие "Завод им.В.Я.Климова"
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 Научно-производственное предприятие "Завод им.В.Я.Климова" filed Critical Научно-производственное предприятие "Завод им.В.Я.Климова"
Priority to RU94028910/06A priority Critical patent/RU2096631C1/en
Publication of RU94028910A publication Critical patent/RU94028910A/en
Application granted granted Critical
Publication of RU2096631C1 publication Critical patent/RU2096631C1/en

Links

Abstract

FIELD: aviation; exhaust devices operating in hot media. SUBSTANCE: inner fairing has holes uniformly spaced over surface and accommodating cups made to suit outer profile of struts fitted radially with clearance through cups into fairing and connected with inner surface of fairing by means of Z-shaped thin-walled dampers. EFFECT: enhanced reliability of operation of exhaust unit. 1 dwg

Claims (1)

Выходное устройство газотурбинного двигателя относится к области авиации, в частности к конструкции выходных устройств, но может быть использовано в любых конструкциях, работающих в горячих средах. Цель изобретения - повышение надежности работы выхлопного устройства ГТД - достигается тем, что внутренний обтекатель выполнен с равнорасположенными по поверхности отверстиями, в которые установлены манжеты, выполненные по форме наружного профиля стоек, входящие радиально с зазором через манжеты внутрь обтекателя и соединены с внутренней поверхностью обтекателя при помощи Z-образных тонкостенных демпферов. 1 ил.The output device of a gas turbine engine belongs to the field of aviation, in particular, to the design of output devices, but can be used in any structures operating in hot environments. The purpose of the invention is to increase the reliability of the GTE exhaust device - it is achieved by the fact that the inner fairing is made with holes equally spaced on the surface, in which cuffs are installed, made in the shape of the outer profile of the struts, radially entering with a clearance through the cuffs inside the fairing and connected to the inner surface of the fairing help Z-shaped thin-walled dampers. 1 ill.
RU94028910/06A 1994-07-28 1994-07-28 Gas-turbine engine exhaust unit RU2096631C1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
RU94028910/06A RU2096631C1 (en) 1994-07-28 1994-07-28 Gas-turbine engine exhaust unit

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
RU94028910/06A RU2096631C1 (en) 1994-07-28 1994-07-28 Gas-turbine engine exhaust unit

Publications (2)

Publication Number Publication Date
RU94028910A true RU94028910A (en) 1996-05-27
RU2096631C1 RU2096631C1 (en) 1997-11-20

Family

ID=20159276

Family Applications (1)

Application Number Title Priority Date Filing Date
RU94028910/06A RU2096631C1 (en) 1994-07-28 1994-07-28 Gas-turbine engine exhaust unit

Country Status (1)

Country Link
RU (1) RU2096631C1 (en)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2441918A1 (en) * 2010-10-18 2012-04-18 Siemens Aktiengesellschaft Gas turbine annular diffuser
RU183942U1 (en) * 2018-04-02 2018-10-09 Публичное Акционерное Общество "Одк-Сатурн" EXHAUST DEVICE FOR A SHIP GAS TURBINE ENGINE

Also Published As

Publication number Publication date
RU2096631C1 (en) 1997-11-20

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Legal Events

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PD4A Correction of name of patent owner
PD4A Correction of name of patent owner
QZ4A Changes in the licence of a patent

Effective date: 19981202