RU2005115545A - DEVICE FOR DETERMINING CHARACTERISTICS AND BOUNDARIES OF STABLE OPERATION OF A COMPRESSOR IN A GAS-TURBINE ENGINE (GTE) SYSTEM - Google Patents

DEVICE FOR DETERMINING CHARACTERISTICS AND BOUNDARIES OF STABLE OPERATION OF A COMPRESSOR IN A GAS-TURBINE ENGINE (GTE) SYSTEM Download PDF

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Publication number
RU2005115545A
RU2005115545A RU2005115545/06A RU2005115545A RU2005115545A RU 2005115545 A RU2005115545 A RU 2005115545A RU 2005115545/06 A RU2005115545/06 A RU 2005115545/06A RU 2005115545 A RU2005115545 A RU 2005115545A RU 2005115545 A RU2005115545 A RU 2005115545A
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RU
Russia
Prior art keywords
boundaries
compressor
turbine engine
stable operation
gte
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Application number
RU2005115545/06A
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Russian (ru)
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RU2297612C2 (en
Inventor
к Лев Иванович Семерн (RU)
Лев Иванович Семерняк
Лев Степанович Безгин (RU)
Лев Степанович Безгин
Original Assignee
Федеральное государственное унитарное предпри тие"Центральный институт авиационного моторостроени им. П.И. Баранова" (RU)
Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения им. П.И. Баранова"
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Application filed by Федеральное государственное унитарное предпри тие"Центральный институт авиационного моторостроени им. П.И. Баранова" (RU), Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения им. П.И. Баранова" filed Critical Федеральное государственное унитарное предпри тие"Центральный институт авиационного моторостроени им. П.И. Баранова" (RU)
Priority to RU2005115545/06A priority Critical patent/RU2297612C2/en
Publication of RU2005115545A publication Critical patent/RU2005115545A/en
Application granted granted Critical
Publication of RU2297612C2 publication Critical patent/RU2297612C2/en

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Claims (1)

Устройство для определения характеристик и границы устойчивой работы компрессора в системе газотурбинного двигателя, содержащее источник тепловой энергии, регуляторы расходов топлива, окислителя, воды и регулирующие дроссели, отличающееся тем, что источником тепловой энергии является камера сгорания, выполненная по типу камеры сгорания жидкостного ракетного двигателя, при этом за камерой сгорания последовательно установлены секция подвода воды, включающая канал подвода воды, испарительная камера, секция распределения потока парогазовой смеси по каналам, причем в каждом из этих каналов установлены регулирующие дроссели.A device for determining the characteristics and boundaries of the stable operation of a compressor in a gas turbine engine system, comprising a heat source, fuel, oxidizer, water flow regulators and control chokes, characterized in that the heat source is a combustion chamber, made like a liquid propellant combustion chamber, at the same time, behind the combustion chamber, a water supply section is installed sequentially, including a water supply channel, an evaporation chamber, a steam flow distribution section charge mixture through the channels, and in each of these channels control chokes are installed.
RU2005115545/06A 2005-05-24 2005-05-24 Device for determination of characteristics and boundaries of steady operation of compressor in gas-turbine engine system RU2297612C2 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
RU2005115545/06A RU2297612C2 (en) 2005-05-24 2005-05-24 Device for determination of characteristics and boundaries of steady operation of compressor in gas-turbine engine system

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
RU2005115545/06A RU2297612C2 (en) 2005-05-24 2005-05-24 Device for determination of characteristics and boundaries of steady operation of compressor in gas-turbine engine system

Publications (2)

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RU2005115545A true RU2005115545A (en) 2006-11-27
RU2297612C2 RU2297612C2 (en) 2007-04-20

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RU2005115545/06A RU2297612C2 (en) 2005-05-24 2005-05-24 Device for determination of characteristics and boundaries of steady operation of compressor in gas-turbine engine system

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RU (1) RU2297612C2 (en)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2488086C2 (en) * 2011-10-24 2013-07-20 Федеральное государственное бюджетное образовательное учреждение высшего профессионального образования "Уфимский государственный авиационный технический университет" Method and device to determine characteristics and border of stable compressor operation within gas turbine engine
RU178985U1 (en) * 2017-10-17 2018-04-24 Акционерное общество "ОДК-Авиадвигатель" BENCH FOR TESTING COMBUSTION CHAMBERS OF GAS-TURBINE ENGINES

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RU2297612C2 (en) 2007-04-20

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MM4A The patent is invalid due to non-payment of fees

Effective date: 20090525