RU92016398A - POWER INSTALLATION FOR AIRPLANE - Google Patents

POWER INSTALLATION FOR AIRPLANE

Info

Publication number
RU92016398A
RU92016398A RU92016398/23A RU92016398A RU92016398A RU 92016398 A RU92016398 A RU 92016398A RU 92016398/23 A RU92016398/23 A RU 92016398/23A RU 92016398 A RU92016398 A RU 92016398A RU 92016398 A RU92016398 A RU 92016398A
Authority
RU
Russia
Prior art keywords
section
fan
pressure turbine
blower fan
turbine unit
Prior art date
Application number
RU92016398/23A
Other languages
Russian (ru)
Other versions
RU2108941C1 (en
Inventor
Поль Майкл Бевилакуа
Поль Ноултон Шамперт
Original Assignee
Локхид Корпорейшн
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
Priority claimed from US07/521,211 external-priority patent/US5209428A/en
Application filed by Локхид Корпорейшн filed Critical Локхид Корпорейшн
Publication of RU92016398A publication Critical patent/RU92016398A/en
Application granted granted Critical
Publication of RU2108941C1 publication Critical patent/RU2108941C1/en

Links

Claims (1)

Изобретение касается силовой установки для самолета типа СКВП V/STOL, конкретнее трубовентиляторного двигателя, включающего в себя вентиляторную секцию, компрессорную секцию, камеру сгорания, турбинную секцию и сопло. Турбинная секция содержит турбинный блок низкого давления, соединенный и приводящий в действие вентиляторную секцию, и турбинный блок высокого давления, соединенный и приводящий в действие компрессорную секцию. Нагнетательный вентилятор соединен с вентиляторной секцией посредством ведущего вала. Муфта установлена для соединения нагнетательного вентилятора от вентиляторной секции. Механизм служит для отбора дополнительной мощности от турбинного блока низкого давления турбинной секции для привода нагнетательного вентилятора, который увеличивает тягу главного двигателя для работы самолета типа СКВП.The invention relates to a power plant for an aircraft of the type VCR / STOL; more specifically, a pipe fan engine comprising a fan section, a compressor section, a combustion chamber, a turbine section and a nozzle. The turbine section contains a low pressure turbine unit, connected and driving the fan section, and a high pressure turbine unit, connected and driving the compressor section. The blower fan is connected to the fan section via a drive shaft. A coupling is installed to connect the blower fan from the fan section. The mechanism serves to take additional power from the low-pressure turbine unit of the turbine section to drive the blower fan, which increases the thrust of the main engine for the operation of an aircraft type STEC.
RU92016398/28A 1990-05-07 1991-02-22 Power plant for short vertical take-off and landing aircraft RU2108941C1 (en)

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
US521,211 1983-08-08
US521.211 1990-05-07
US07/521,211 US5209428A (en) 1990-05-07 1990-05-07 Propulsion system for a vertical and short takeoff and landing aircraft
PCT/US1991/001145 WO1991017083A1 (en) 1990-05-07 1991-02-22 Propulsion system for a vertical and short takeoff and landing aircraft

Publications (2)

Publication Number Publication Date
RU92016398A true RU92016398A (en) 1996-05-20
RU2108941C1 RU2108941C1 (en) 1998-04-20

Family

ID=24075841

Family Applications (1)

Application Number Title Priority Date Filing Date
RU92016398/28A RU2108941C1 (en) 1990-05-07 1991-02-22 Power plant for short vertical take-off and landing aircraft

Country Status (7)

Country Link
US (1) US5209428A (en)
EP (1) EP0527956B1 (en)
JP (1) JP2647258B2 (en)
DE (1) DE69126132T2 (en)
IL (1) IL97434A (en)
RU (1) RU2108941C1 (en)
WO (1) WO1991017083A1 (en)

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RU2522208C1 (en) * 2012-01-17 2014-07-10 Юнайтед Текнолоджис Корпорейшн Gas turbine engine pylon assembly and gas turbine engine system

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