RU2007147567A - FAN AIRCRAFT ENGINE - Google Patents

FAN AIRCRAFT ENGINE Download PDF

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Publication number
RU2007147567A
RU2007147567A RU2007147567/06A RU2007147567A RU2007147567A RU 2007147567 A RU2007147567 A RU 2007147567A RU 2007147567/06 A RU2007147567/06 A RU 2007147567/06A RU 2007147567 A RU2007147567 A RU 2007147567A RU 2007147567 A RU2007147567 A RU 2007147567A
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RU
Russia
Prior art keywords
fan
stage
compressor
aircraft
turbocharger
Prior art date
Application number
RU2007147567/06A
Other languages
Russian (ru)
Other versions
RU2379523C2 (en
Inventor
Николай Борисович Болотин (RU)
Николай Борисович Болотин
Original Assignee
Николай Борисович Болотин (RU)
Николай Борисович Болотин
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.)
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Application filed by Николай Борисович Болотин (RU), Николай Борисович Болотин filed Critical Николай Борисович Болотин (RU)
Priority to RU2007147567/06A priority Critical patent/RU2379523C2/en
Publication of RU2007147567A publication Critical patent/RU2007147567A/en
Application granted granted Critical
Publication of RU2379523C2 publication Critical patent/RU2379523C2/en

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Abstract

1. Винтовентиляторный авиационный двигатель, содержащий турбокомпрессор с корпусом, компрессором, камерой сгорания, выход из которой соединен газовым трактом с турбиной, и двухступенчатый винтовентилятор, отличающийся тем, одна ступень винтовентилятора соединена с компрессором через магнитную муфту, а другая ступень винтовентилятора соединена с первой ступенью через ревенсивный редуктор. ! 2. Винтовентиляторный авиационный двигатель по п.1, отличающийся тем, что магнитная муфта выполнена на корпусе турбокомпрессора и содержит ведомую полумуфту, установленную в компрессоре, например, на его рабочих лопатках и ведомую полумуфту, установленную на корпусе турбокомпрессора. ! 3. Винтовентиляторный авиационный двигатель по п.1 или 2, отличающийся тем, что ступени винтовентилятора размещены внутри обтекателя. 1. Aircraft fan engine containing a turbocharger with a housing, a compressor, a combustion chamber, the output of which is connected by a gas path to the turbine, and a two-stage fan, characterized in that one stage of the fan is connected to the compressor through a magnetic coupling, and the other stage of the fan is connected to the first stage through a gearbox. ! 2. Aircraft fan engine according to claim 1, characterized in that the magnetic coupling is made on the turbocharger housing and contains a driven coupling half installed in the compressor, for example, on its working blades and a driven coupling half mounted on the turbocharger housing. ! 3. Aircraft fan engine according to claim 1 or 2, characterized in that the stages of the fan are located inside the fairing.

Claims (3)

1. Винтовентиляторный авиационный двигатель, содержащий турбокомпрессор с корпусом, компрессором, камерой сгорания, выход из которой соединен газовым трактом с турбиной, и двухступенчатый винтовентилятор, отличающийся тем, одна ступень винтовентилятора соединена с компрессором через магнитную муфту, а другая ступень винтовентилятора соединена с первой ступенью через ревенсивный редуктор.1. Aircraft fan engine containing a turbocharger with a housing, a compressor, a combustion chamber, the output of which is connected by a gas path to the turbine, and a two-stage fan, characterized in that one stage of the fan is connected to the compressor through a magnetic coupling, and the other stage of the fan is connected to the first stage through a gearbox. 2. Винтовентиляторный авиационный двигатель по п.1, отличающийся тем, что магнитная муфта выполнена на корпусе турбокомпрессора и содержит ведомую полумуфту, установленную в компрессоре, например, на его рабочих лопатках и ведомую полумуфту, установленную на корпусе турбокомпрессора.2. Aircraft fan engine according to claim 1, characterized in that the magnetic coupling is made on the turbocharger housing and contains a driven coupling half installed in the compressor, for example, on its working blades and a driven coupling half mounted on the turbocharger housing. 3. Винтовентиляторный авиационный двигатель по п.1 или 2, отличающийся тем, что ступени винтовентилятора размещены внутри обтекателя. 3. Aircraft fan engine according to claim 1 or 2, characterized in that the stages of the fan are located inside the fairing.
RU2007147567/06A 2007-12-19 2007-12-19 Aircraft propfan engine RU2379523C2 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
RU2007147567/06A RU2379523C2 (en) 2007-12-19 2007-12-19 Aircraft propfan engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
RU2007147567/06A RU2379523C2 (en) 2007-12-19 2007-12-19 Aircraft propfan engine

Publications (2)

Publication Number Publication Date
RU2007147567A true RU2007147567A (en) 2009-06-27
RU2379523C2 RU2379523C2 (en) 2010-01-20

Family

ID=41026686

Family Applications (1)

Application Number Title Priority Date Filing Date
RU2007147567/06A RU2379523C2 (en) 2007-12-19 2007-12-19 Aircraft propfan engine

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RU (1) RU2379523C2 (en)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2672985C2 (en) * 2017-03-20 2018-11-21 Владимир Владимирович Черепанов Combustion chamber for gas turbine installation

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Publication number Publication date
RU2379523C2 (en) 2010-01-20

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Legal Events

Date Code Title Description
FA92 Acknowledgement of application withdrawn (lack of supplementary materials submitted)

Effective date: 20090521

FZ9A Application not withdrawn (correction of the notice of withdrawal)

Effective date: 20090730