SU1434854A2 - Cooled blade of gas turbine - Google Patents

Cooled blade of gas turbine Download PDF

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Publication number
SU1434854A2
SU1434854A2 SU864167276A SU4167276A SU1434854A2 SU 1434854 A2 SU1434854 A2 SU 1434854A2 SU 864167276 A SU864167276 A SU 864167276A SU 4167276 A SU4167276 A SU 4167276A SU 1434854 A2 SU1434854 A2 SU 1434854A2
Authority
SU
USSR - Soviet Union
Prior art keywords
shell
deflector
cavity
gas turbine
cooled blade
Prior art date
Application number
SU864167276A
Other languages
Russian (ru)
Inventor
О.Г. Жирицкий
В.Е. Беляев
А.С. Косой
М.С. Косой
Original Assignee
Предприятие П/Я А-1469
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 Предприятие П/Я А-1469 filed Critical Предприятие П/Я А-1469
Priority to SU864167276A priority Critical patent/SU1434854A2/en
Application granted granted Critical
Publication of SU1434854A2 publication Critical patent/SU1434854A2/en

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Abstract

Изобретение м.б, использовано ,;в авиациОниых двигател х Цель изобретени  - упрощение изготовлени  лопатки . Лопатка содержит полую оболочку 1 и установленный в ее полости 2 дефлектор 3. Торец А дефлектора консольно закреплен в оболочке 1«Оболочка 1 снабжена бобыйкой 5, образующей с. ее внутренней поверхностью профильную щель, торец 8 дефлектора размещен в этой щели. Бобышка 5 со стороны полости 2 снабжена поперечны- ш пазами 9, Воздух поступает в дефлектор 3, перетекает в полость 2 и проходит ме /ду дефлр.ктором внутренней поверхностью оболочки 1, охлажда  оболочку. 2 ил.Invention mb, used,; in aircraft engines. The purpose of the invention is to simplify the manufacture of a blade. The paddle contains a hollow shell 1 and a deflector 3 installed in its cavity 2. The end face A of the deflector is cantilevered in the shell 1 “The shell 1 is provided with a leg 5, which forms c. its internal surface profile gap, the end face 8 of the deflector is placed in this gap. Lug 5 on the side of cavity 2 is provided with transverse slots 9, Air enters deflector 3, flows into cavity 2 and passes through the inner surface of shell 1 to the deflector of the shell 1, cooling the shell. 2 Il.

Description

1212

Фив.Thebes.

SU864167276A 1986-12-24 1986-12-24 Cooled blade of gas turbine SU1434854A2 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
SU864167276A SU1434854A2 (en) 1986-12-24 1986-12-24 Cooled blade of gas turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
SU864167276A SU1434854A2 (en) 1986-12-24 1986-12-24 Cooled blade of gas turbine

Related Parent Applications (1)

Application Number Title Priority Date Filing Date
SU1261359A Addition SU278988A1 (en) METHOD OF MANUFACTURING MULTILAYERED GLASS

Publications (1)

Publication Number Publication Date
SU1434854A2 true SU1434854A2 (en) 1991-06-23

Family

ID=21275124

Family Applications (1)

Application Number Title Priority Date Filing Date
SU864167276A SU1434854A2 (en) 1986-12-24 1986-12-24 Cooled blade of gas turbine

Country Status (1)

Country Link
SU (1) SU1434854A2 (en)

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
Авторское свидетельство СССР 1261359, кл. F 01 D 5/18, 1985. *

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