-
公开(公告)号：JP2003206806A
公开(公告)日：2003-07-25
申请号：JP2002008072
申请日：2002-01-16
Applicant: NAT AEROSPACE LAB
Inventor： SAITO YOSHIO , ENDO MASANORI , MATSUDA YUKIO , SUGIYAMA SHICHIKEI , TAGASHIRA TAKESHI
IPC: B64C29/00 , F02C1/02 , F02C3/10 , F02C3/13 , F02C3/14 , F02C6/08 , F02C7/36 , F02K3/06 , F02K3/075 , F02K3/077 , F02K3/11 , F02K3/12
Abstract: PROBLEM TO BE SOLVED: To provide a silent turbo fan engine of a core engine separation type allowing reduction of noise generated by a control propelling device by using high pressure air as working fluid of a turbine for driving a control fan for controlling a body attitude. SOLUTION: The control fan 17 constituting the control propelling device 4 disposed for controlling the body attitude of the turbo fan engine 1 of the core engine separation type is driven by an air turbine 19 using as the working fluid the high pressure air compressed by a compressor 6 of the core engine 2 and supplied through a duct 10. Speed of the working fluid discharged from the control fan 17 and the air turbine 19 is lower than that of the working fluid discharged from the propelling device 3 for propelling, and is as low as that required for attitude control, so that the noise occurring from the control propelling device 4 is reduced. COPYRIGHT: (C)2003,JPO
-
公开(公告)号：JP2000321122A
公开(公告)日：2000-11-24
申请号：JP13093299
申请日：1999-05-12
Applicant: NAT AEROSPACE LAB
Inventor： MATSUDA YUKIO , ENDO MASANORI
Abstract: PROBLEM TO BE SOLVED: To obtain highly accurate measurements conveniently simply through measurement during operation by measuring the time being elapsed until a plurality of rotor blades are detected through rotor blade tip detectors after starting measurement of an arbitrary time and then storing, operating and controlling a measured time data. SOLUTION: The vibration measuring apparatus comprises rotor blade tip detectors S1, S2,..., Sn arranged on the rotational periphery of rotor blades B1, B2,..., Bn, output amplifiers A1, A2,..., An, counters C1, C2,..., Cn, memory means M1, M2,..., Mn, and an operation control section CTR. The counter begins measurement of time at an arbitrary moment of time and stores the time elapsed before an output signal is received from the rotor blade tip detectors sequentially in the memory means. Timing of a series of detection signals from rotor blade tip detectors is processed totally and statistically. Vibration of the rotor blade is calculated from the measurement of rotor blade passing time under a situation of a rotary machine where the rotor blade is not displaced from a regular position and the actual measurement of each rotor blade passing time at the measuring time.
-
Patent Agency Ranking
公开(公告)号：JPH0719068A
公开(公告)日：1995-01-20
申请号：JP16488093
申请日：1993-07-02
Applicant: NAT AEROSPACE LAB , ISHIKAWAJIMA HARIMA HEAVY IND
Inventor： ENDO MASANORI , ENDO MAKOTO
Abstract: PURPOSE:To actuate and cool auxiliary machinery efficiently, and heighten comprehensive efficiency of an engine by driving an auxiliary turbine in rotation by taking compressed air of a compressor outside of an engine body, and actuating the auxiliary machinery for the engine by the auxiliary turbine. CONSTITUTION:When an engine body 20 is operated, respective low pressure air and high pressure compressed air are bled from respective low pressure and high pressure compressors. Then, an air directional control valve 22 is switched according to the number of revolutions of the engine body 20, and respective low pressure and high pressure bleed air pipelines 21A and 21B are selected. Selected bleed air is supplied to an air regulating means 23, and here, an air quantity to be transferred to an auxiliary turbine 24 is regulated according to specifications of respective auxiliary machinery. Afterwards, the auxiliary turbine 24 is driven in rotation by the bleed air, and the respective auxiliary machinery, for example, a generator 27, a lubricating oil pump 28, a fuel pump 29 and the like are actuated. On the other hand, air whose temperature is lowered by being used for driving in rotation is discharged to an air discharge pipe 24b, and is used to cool a heat exchanger 25 or the engine body 20.
-
公开(公告)号：JP2003206746A
公开(公告)日：2003-07-25
申请号：JP2002008071
申请日：2002-01-16
Applicant: NAT AEROSPACE LAB
Inventor： SAITO YOSHIO , ENDO MASANORI , MATSUDA YUKIO , SUGIYAMA SHICHIKEI , TAGASHIRA TAKESHI
IPC: B64C29/00 , F02C1/02 , F02C3/10 , F02C3/13 , F02C6/08 , F02C7/36 , F02K3/00 , F02K3/06 , F02K3/075 , F02K3/077 , F02K3/12
Abstract: PROBLEM TO BE SOLVED: To provide a multi-fan type core engine separate type turbofan engine to reduce the manufacturing cost of a turbofan engine with simple structure by using high-pressure air as a working fluid of a turbine driving a fan. SOLUTION: The turbine driving the fan 11 which constitutes a propulsion unit 3 of the multi-fan type core engine separate type turbofan engine 1 is an air turbine 13 driven by supplying a part of high-pressure air compressed by a compressor 5 of a core engine 2 through a duct 9. Since the working fluid of the air turbine 13 driving the fan 11 is not high-temperature combustion gas, it does not need to use an expensive heat-resistant material, can manufacture the propulsion unit 3 at low cost, and can simplify structure and operation control. COPYRIGHT: (C)2003,JPO
-
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.
-
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.
-
公开(公告)号：JPS63313007A
公开(公告)日：1988-12-21
申请号：JP14993887
申请日：1987-06-16
Applicant: NAT AEROSPACE LAB
Inventor： MATSUDA YUKIO , ENDO MASANORI
Abstract: PURPOSE:To easily measure the axial elongation quantity of a rotary body at an optional position with high accuracy over a wide measurement range by providing a mark which is fitted slantingly to the axial direction of the rotary body. CONSTITUTION:Marks which are parallel to, for example, the shaft of the rotary body are drawn on the mark 2 which is slanted properly to the axial direction and a reference mark 3. Sensors 4 and 5 each generate one output for one turn every time the marks 2 and 3 pass in front of the sensors 4 and 5. Here, the sensor 5 generates its output signal invariably at a reference mark position regardless of the elongation of the shaft 1, but the output signal of the sensor 4 varies in time interval with the output signal of the sensor 5 because it moves axially as shown by a dotted line in a figure as the shaft 1 is elongated. Therefore, the elongation quantity of the shaft 1 is calculated from the time difference from a measurement time in a no- elongation reference time, the rotating speed (found from the interval between the output signals of the sensors 4 and 5), and the external diameter of the shaft 1. Further, the sensors can be arranged in parallel to the rotary body, so a measurement is taken at an optional position.
-
-
-
-
-
-
Search Results
7
records
(took 0.027 seconds)
