RU1772359C - Outlet unit of turbo-machine - Google Patents

Outlet unit of turbo-machine

Info

Publication number
RU1772359C
RU1772359C SU904821921A SU4821921A RU1772359C RU 1772359 C RU1772359 C RU 1772359C SU 904821921 A SU904821921 A SU 904821921A SU 4821921 A SU4821921 A SU 4821921A RU 1772359 C RU1772359 C RU 1772359C
Authority
RU
Russia
Prior art keywords
area
shell
turbo
cowl
entrance
Prior art date
Application number
SU904821921A
Other languages
Russian (ru)
Inventor
Георгий Георгиевич Миронов
Original Assignee
Научно-производственное объединение "Наука"
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 объединение "Наука" filed Critical Научно-производственное объединение "Наука"
Priority to SU904821921A priority Critical patent/RU1772359C/en
Application granted granted Critical
Publication of RU1772359C publication Critical patent/RU1772359C/en

Links

Landscapes

  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Jet Pumps And Other Pumps (AREA)

Abstract

Использование: турбохолодильные системы кондиционировани  воздуха летательных аппаратов. Сущность изобретени : выходное устройство турбомашины состоит из диффузорного патрубка 1. обечайки 2, закрепленной в нем на стойках 3, обтекател  4, присоединенного к втулке 5 гурбины, при этом обечайка 2 расположена вокруг обтекател  4 с образованием кольцевого зазора и соединена с последним лопатками 6, причем площадь кольцевого зазора на входе в обечайку равна 10...15% площади входного сечени  патрубка 1, площадь сечени  на выходе из нее равна или меньше площади на ее входе, а образующа  обтекател  в меридиональном сечении описана окружностью или эллипсом. 3 ил.Usage: turbo-refrigeration air conditioning systems of aircraft. SUMMARY OF THE INVENTION: The output device of a turbomachine consists of a diffuser nozzle 1. A shell 2 mounted thereon on a strut 3, a cowl 4 connected to a sleeve 5 of a turbine, and a shell 2 is located around the cowl 4 to form an annular gap and connected to the last vanes 6, moreover, the area of the annular gap at the entrance to the shell is equal to 10 ... 15% of the area of the inlet section of the pipe 1, the sectional area at the exit of it is equal to or less than the area at its entrance, and the circumference forming in the meridional section is described circumferentially Stew or ellipse. 3 ill.

Description

Ф(/8. /F (/ 8. /

SU904821921A 1990-04-04 1990-04-04 Outlet unit of turbo-machine RU1772359C (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
SU904821921A RU1772359C (en) 1990-04-04 1990-04-04 Outlet unit of turbo-machine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
SU904821921A RU1772359C (en) 1990-04-04 1990-04-04 Outlet unit of turbo-machine

Publications (1)

Publication Number Publication Date
RU1772359C true RU1772359C (en) 1992-10-30

Family

ID=21512382

Family Applications (1)

Application Number Title Priority Date Filing Date
SU904821921A RU1772359C (en) 1990-04-04 1990-04-04 Outlet unit of turbo-machine

Country Status (1)

Country Link
RU (1) RU1772359C (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2472003C1 (en) * 2011-06-08 2013-01-10 Открытое акционерное общество "Научно-производственное объединение "Сатурн" (ОАО "НПО "Сатурн") Outlet device of turbine of aircraft gas-turbine engine

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
Масл нников М.М. Авиационные газотурбинные двигатели. М.: Машиностроение, 1975, С.446, рис.14.1(б). *

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2472003C1 (en) * 2011-06-08 2013-01-10 Открытое акционерное общество "Научно-производственное объединение "Сатурн" (ОАО "НПО "Сатурн") Outlet device of turbine of aircraft gas-turbine engine

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