RU94026915A - Turbojet - Google Patents

Turbojet

Info

Publication number
RU94026915A
RU94026915A RU94026915/06A RU94026915A RU94026915A RU 94026915 A RU94026915 A RU 94026915A RU 94026915/06 A RU94026915/06 A RU 94026915/06A RU 94026915 A RU94026915 A RU 94026915A RU 94026915 A RU94026915 A RU 94026915A
Authority
RU
Russia
Prior art keywords
wall
combustion chamber
additional combustion
engine
turbojet
Prior art date
Application number
RU94026915/06A
Other languages
Russian (ru)
Other versions
RU2109974C1 (en
Inventor
А.П. Петренко
Original Assignee
А.П. Петренко
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 А.П. Петренко filed Critical А.П. Петренко
Priority to RU94026915/06A priority Critical patent/RU2109974C1/en
Publication of RU94026915A publication Critical patent/RU94026915A/en
Application granted granted Critical
Publication of RU2109974C1 publication Critical patent/RU2109974C1/en

Links

Abstract

FIELD: manufacture of aircraft engines. SUBSTANCE: TURBOJET engine is provided with air preheater mounted in passage supplying compressed air to additional combustion chamber which is arranged in after-turbine space; wall of outlet nozzle is used as wall of additional combustion chamber. EFFECT: increased thrust of engine.

Claims (1)

Изобретение относится к авиадвигателестроению и может найти применение на летательных аппаратах. Цель: повышение тяги двигателя. Сущность изобретения: турбореактивный двигатель снабжен воздухоподогревателями в канале подачи сжатого воздуха в дополнительную камеру сгорания, которая установлена в затурбинном пространстве, причем стенка выходного сопла является стенкой дополнительной камеры сгорания.The invention relates to aircraft engine manufacturing and may find application in aircraft. Goal: increase engine thrust. The inventive turbojet engine is equipped with air heaters in the channel for supplying compressed air to the additional combustion chamber, which is installed in the turbine space, and the wall of the outlet nozzle is the wall of the additional combustion chamber.
RU94026915/06A 1994-07-15 1994-07-15 Turbojet engine RU2109974C1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
RU94026915/06A RU2109974C1 (en) 1994-07-15 1994-07-15 Turbojet engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
RU94026915/06A RU2109974C1 (en) 1994-07-15 1994-07-15 Turbojet engine

Publications (2)

Publication Number Publication Date
RU94026915A true RU94026915A (en) 1997-05-20
RU2109974C1 RU2109974C1 (en) 1998-04-27

Family

ID=20158588

Family Applications (1)

Application Number Title Priority Date Filing Date
RU94026915/06A RU2109974C1 (en) 1994-07-15 1994-07-15 Turbojet engine

Country Status (1)

Country Link
RU (1) RU2109974C1 (en)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106677901A (en) * 2015-11-10 2017-05-17 熵零股份有限公司 Aeroengine
CN110985207A (en) * 2019-12-30 2020-04-10 绵阳小巨人动力设备有限公司 Miniature double-combustion-chamber variable-circulation turbojet engine

Also Published As

Publication number Publication date
RU2109974C1 (en) 1998-04-27

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Legal Events

Date Code Title Description
MM4A The patent is invalid due to non-payment of fees

Effective date: 20060716