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公开(公告)号：JPH02283821A
公开(公告)日：1990-11-21
申请号：JP10536589
申请日：1989-04-25
Applicant: NAT AEROSPACE LAB
Inventor： SAITO YOSHIO , ENDO MASANORI , SUGAWARA NOBORU , YAMAMOTO KAZUTOMI
Abstract: PURPOSE:To facilitate the manufacture and to arrange a propulsion device in a required position by constituting a core engine and the propulsion device separately, and by connecting them through a high pressure air duct. CONSTITUTION:A turbo fan engine 1 is constituted of a core engine 2 and a propulsion device 3 which is divided from the core engine 2. In the core engine 2, there are provided a compressor 5, a burner 6 and turbine 7 inside a case 4, and the turbine 7 is connected to the compressor 5 through a shaft 8. Thus, air which is compressed by the compressor 5 is partially introduced to the burner 6 and the turbine 7, and the rest is led to the duct 9. In the propulsion device 3, there are provided a fan 11 inside a shroud 10 and, the burner 13 and the turbine 14 inside the case 12 which is coaxial with the fan 11, and the duct 9 is connected to the burner 13. Thus, the fuel is burned by using the high pressure air in the burner 13 through the duct 9, and thereby the turbine 14 is driven.
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公开(公告)号：JPH02283822A
公开(公告)日：1990-11-21
申请号：JP10536689
申请日：1989-04-25
Applicant: NAT AEROSPACE LAB
Inventor： SAITO YOSHIO , ENDO MASANORI , SUGAWARA NOBORU , YAMAMOTO KAZUTOMI
Abstract: PURPOSE:To reduce the exhaust noise especially by using air for rotating a fan of an auxiliary propulsion device after passing high pressure air from a main compressor to a sub-compressor of a by-pass passage at the time of low speed, and by exhausting the high pressure air from the main compressor, from a main passage at the time of high speed. CONSTITUTION:A main compressor 3 is arranged in the front between an outer cylinder 1 and an inner cylinder 2, and a main passage 4 at the downstream side of the main compressor 3. At the downstream side of the main passage 4, a sub-passage 6 which is communicated with the main passage 4 is arranged through a primary shutter 5. There is provided a by-pass passage 9 which is communicated with the main passage 4 through a secondary shutter 7, and with the sub-passage 6 through a third shutter 8. A main combustion chamber 10 and a main turbine 11 are arranged at the sub-passage 6, and a sub- compressor 12, a sub-combustion chamber 13 and a sub-turbine 14 are arranged at the by-pass passage 9. A duct 15 is connected to the downstream side of the sub-compressor 12, and the duct 15 is connected to the auxiliary propulsion device 17 through a high pressure air controller 16.
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公开(公告)号：JPH02283847A
公开(公告)日：1990-11-21
申请号：JP10536489
申请日：1989-04-25
Applicant: NAT AEROSPACE LAB
Inventor： SAITO YOSHIO , TAMURA ATSUHIRO , SUGAWARA NOBORU , YAMAMOTO KAZUTOMI
Abstract: PURPOSE:To reduce the size of an engine by a method wherein, in a title engine which cools intake air through heat-exchange of it with liquid hydrogen and separates liquid oxygen, oxygen in the air taken in during fly is liquefied and separated by means of a turbine. CONSTITUTION:In a rocket, liquid hydrogen and liquid oxygen from a liquefied hydrogen tank 2 and a liquid oxygen tank 3 are burnt in the combustion chamber of a rocket engine 4, and injected to produce thrust. In this case, an oxygen liquefying device 6 adapted to compensate for deficiency in liquid oxygen in the tank 3 is provided. The oxygen liquefying device 6 is provided with a first heat exchanger 8 to cool air taken in through an air intake port 7 by means of liquid oxygen, a turbine 9 to cool cooling air to temperature lower than an oxygen liquefying temperature and separate liquefied oxygen, a compressor 10 to boost air from which oxygen is separated, and a second heat exchanger 11 to heat-exchange with boosted air. Liquid oxygen separated by the turbine 9 is fed to the tank 3 with the aid of a pump 15.
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