SU1140551A1 - METHOD FOR DETERMINING A TURBO-REACTIVE MOTOR WITH A FORCING CAMERA - Google Patents

METHOD FOR DETERMINING A TURBO-REACTIVE MOTOR WITH A FORCING CAMERA

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Publication number
SU1140551A1
SU1140551A1 SU3534361/06A SU3534361A SU1140551A1 SU 1140551 A1 SU1140551 A1 SU 1140551A1 SU 3534361/06 A SU3534361/06 A SU 3534361/06A SU 3534361 A SU3534361 A SU 3534361A SU 1140551 A1 SU1140551 A1 SU 1140551A1
Authority
SU
USSR - Soviet Union
Prior art keywords
pressure
chamber
mixing
beginning
determining
Prior art date
Application number
SU3534361/06A
Other languages
Russian (ru)
Inventor
В.М. Борщанский
В.О. Боровик
Л.Н. Дружинин
Original Assignee
В.М. Борщанский
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 В.М. Борщанский filed Critical В.М. Борщанский
Priority to SU3534361/06A priority Critical patent/SU1140551A1/en
Application granted granted Critical
Publication of SU1140551A1 publication Critical patent/SU1140551A1/en

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Abstract

Способ определения тяги турбореактивного двигателя с форсажной камерой, включающий измерение атмосферного давления, полного давления газа за турбиной и статистического давления в конце форсажной камеры и вычисление тяги по указанным параметрам, отличающийся тем, что, с целью повышения точности определения тяги двухконтурного двигателя со смещением потоков, дополнительно измеряют полное давление воздуха в наружном контуре двигателя и статическое давление газа в начале камеры смещения, определяют полное давление смешения как осредненное по площади полное давление в начале камеры смешения, отношение статического давления в начале камеры смешения и полного давления смешения и по указанному отношению корректируют вычисление величины тяги.The method for determining the turbojet thrust engine with an afterburner chamber, including measurement of atmospheric pressure, total gas pressure behind the turbine, and statistical pressure at the end of the afterburner chamber additionally, the total air pressure in the external circuit of the engine and the static gas pressure at the beginning of the displacement chamber are measured, the total mixing pressure is determined as the mean Noe area full pressure at the beginning of the mixing chamber, the static pressure ratio at the beginning of the mixing and complete mixing of the pressure chamber and relative to said corrected value calculating traction.

SU3534361/06A 1983-01-06 1983-01-06 METHOD FOR DETERMINING A TURBO-REACTIVE MOTOR WITH A FORCING CAMERA SU1140551A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
SU3534361/06A SU1140551A1 (en) 1983-01-06 1983-01-06 METHOD FOR DETERMINING A TURBO-REACTIVE MOTOR WITH A FORCING CAMERA

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
SU3534361/06A SU1140551A1 (en) 1983-01-06 1983-01-06 METHOD FOR DETERMINING A TURBO-REACTIVE MOTOR WITH A FORCING CAMERA

Publications (1)

Publication Number Publication Date
SU1140551A1 true SU1140551A1 (en) 2004-08-10

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ID=60540352

Family Applications (1)

Application Number Title Priority Date Filing Date
SU3534361/06A SU1140551A1 (en) 1983-01-06 1983-01-06 METHOD FOR DETERMINING A TURBO-REACTIVE MOTOR WITH A FORCING CAMERA

Country Status (1)

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SU (1) SU1140551A1 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2596413C1 (en) * 2015-03-25 2016-09-10 Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения имени П.И. Баранова" Method of determining thrust in flight of bypass turbojet engine with mixing of flows

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2596413C1 (en) * 2015-03-25 2016-09-10 Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения имени П.И. Баранова" Method of determining thrust in flight of bypass turbojet engine with mixing of flows

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