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1. 发明专利

JP2512256B2 失效
公开(公告)号：JP2512256B2
公开(公告)日：1996-07-03
申请号：JP726092
申请日：1992-01-20
申请人： HITACHI LTD
发明人： TSUKAHARA SATOSHI , HAYASHI NORYUKI , ANZAI SHUNICHI , ISHIBASHI YOJI , UMEZAWA SADAO , SAKURAI SHIGEO , KUMADA KAZUHIKO
IPC分类号： F02C7/18 , F23R3/06

2. 发明专利

JPH0668373B2 失效
公开(公告)号：JPH0668373B2
公开(公告)日：1994-08-31
申请号：JP24983687
申请日：1987-10-05
申请人： HITACHI LTD
发明人： ISHIBASHI YOJI , TSUKAHARA SATOSHI , HAYASHI NORYUKI , SEGAWA YORIHIDE , ANZAI SHUNICHI , KUMADA KAZUHIKO
IPC分类号： F23R3/00

3. 发明专利

JPH06137166A SUPPORTING STRUCTURE FOR GAS TURBINE COMBUSTOR 失效
公开(公告)号：JPH06137166A
公开(公告)日：1994-05-17
申请号：JP28726992
申请日：1992-10-26
申请人： HITACHI LTD
发明人： HAYASHI NORIYUKI , IWAI KAZUMI , ISHIBASHI YOJI , AKATSU SHIGEYUKI , AZUHATA SHIGERU , ITO KAZUYUKI , INNAMI TAMIO , INOUE HIROSHI , YOSHIDA SHOHEI , TSUKAHARA SATOSHI
IPC分类号： F02C7/20 , F23R3/60
摘要： PURPOSE:To improve rigidity and wear resistance of a spring while eliminating air flowing into a tail cylinder from a liner by mounting a separate spring also between the inside of the spring and the liner, in a supporting structure wherein the spring is mounted to an end part of the liner inserted to the tail cylinder. CONSTITUTION:A spring 3, formed by bending a thin plate into a circular arc shape, is mounted on an end peripheral surface of a liner 1 on the side of a tail cylinder 2. Many slits 4 are formed in an axial direction of the liner 1. Further, a rear end part 5 of the spring 3 is spot welded by a spot 6 to the liner 1. Also between the inside of the spring 3 and the liner 1, a similarly formed spring 3' is mounted. In a condition that the liner l is completely inserted into the tail cylinder 2, both the outside/inside springs 3, 3' are overlapped with each other, and also the respective slits 4, 4' are displaced from each other. In this way, rigidity and wear resistance of the spring 3 are improved while eliminating air flowing into the tail cylinder 2 from the liner 1.

4. 发明专利

JPH062847A TURBINE COMBUSTION APPARATUS 失效
公开(公告)号：JPH062847A
公开(公告)日：1994-01-11
申请号：JP16306992
申请日：1992-06-22
申请人： HITACHI LTD
发明人： ITO KAZUYUKI , KOBAYASHI YOSHINOBU , SOMA KENICHI , MURAKAMI TADATAKA , AZUHATA SHIGERU , TANIGUCHI MASAYUKI , TSUKAHARA SATOSHI , KURODA MICHIO
IPC分类号： F23R3/00 , F23R3/26
摘要： PURPOSE:To accurately detect the air feed rate or air-fuel ratio by a method wherein air and fuel are supplied into a combustion chamber, and the flow rate of air supplied by an air supply device is estimated based on the detected results of air flow rate detectors. CONSTITUTION:Air flow rate detectors 11a and 11b are respectively installed at the closest and farthest locations to a communicating path between a fuel feed port 6 and a fuel distribution path 53, and output detected signals 12 to a controller 30. The controller 30 is previously given a map which contains a correspondent relationship between the detected signals 12 showing the air flow rates in the vicinity of the air flow rate detectors 11a and 11b and the flow rate of the whole air flowing into a mixing chamber 2. The controller 30 comprehensively judges the detected signals 12 referring to the map, and estimates the air flow rate to the mixing chamber 2. Then, the controller 30 operates a slide gate 21 based on the estimated result to regulate the air flow rate to an optimum value.

5. 发明专利

JPH0428923A GAS TURBINE COMBUSTOR 失效
公开(公告)号：JPH0428923A
公开(公告)日：1992-01-31
申请号：JP13131290
申请日：1990-05-23
申请人： HITACHI LTD
发明人： TSUKAHARA SATOSHI , KOBAYASHI SHIGEYOSHI
IPC分类号： F23R3/28 , F23R3/36
摘要： PURPOSE:To reduce NOX in the use of an auxiliary combustor for diffusion combustion by using methanol for the combustion in the auxiliary combustor so as to lower the rate at which N2 in the air forms NOX. CONSTITUTION:When the load is in a low range, fuel from a fuel-gas nozzle 4 is used to undergo combustion in an auxiliary combustor 6. When the output is increased, fuel is also fed through a fuel-gas nozzle 5 in order to suppress the rise of NOX; in this case an airflow control valve 11 is adjusted so as to make the fuel-air ratio appropriate and the resulting premixed fuel is made to undergo combustion in the main combustion chamber 7; on the other hand, in the auxiliary combustion chamber 6, the rate of the combustion flow is decreased and the fuel is changed to methanol and supplied for the combustion through a fuel nozzle 3. The change of the fuel to the auxiliary combustor to methanol is effective in reducing NOX, since the highest temperature of the flame in the auxiliary combustor can be reduced. When the equipment is operated for a low output which makes the complete combustion difficult, the use of a fuel which is easy of combustion enables reducing emission of other pollutants such as CO and hydrocarbons.

6. 发明专利

JPH0328606A GAS TURBINE FUEL NOZZLE 失效
公开(公告)号：JPH0328606A
公开(公告)日：1991-02-06
申请号：JP16078189
申请日：1989-06-26
申请人： HITACHI LTD
发明人： HAYASHI NORIYUKI , TSUKAHARA SATOSHI , ISHIBASHI YOJI
IPC分类号： F02C7/232 , F23D11/12 , F23D11/38
摘要： PURPOSE:To prevent the application of heat to the end face of a nozzle and improve reliability and service life by installing a cooling air current path which runs from an upper stream of a rotating blade to the end face of a fuel nozzle in parallel to the rotating blade inside the fuel nozzle. CONSTITUTION:A cooling air current path 16, which runs from the upper stream of a rotating blade 9 to a cooling groove 15 on a nozzle end face, is formed on a rotary equipment cone 7, avoiding an exhaust nozzle 14. This construction makes it possible to use a differential pressure between the upper stream and the downstream of the rotating blade 9 as a drive force so as to let a cooling air flow and discharge the cooling air from a nozzle end face groove 15. It is, therefore, possible to protect the nozzle end face from the heat of flames and hence improve the reliability and device life as well.

7. 发明专利

JPH02267406A FUEL NOZZLE OF GAS TURBINE 失效
公开(公告)号：JPH02267406A
公开(公告)日：1990-11-01
申请号：JP8793789
申请日：1989-04-10
申请人： HITACHI LTD
发明人： ISHIBASHI YOJI , TSUKAHARA SATOSHI , HAYASHI NORIYUKI
IPC分类号： F02C7/232 , F23D11/12
摘要： PURPOSE:To cool a fuel nozzle member and at the same time prevent an exces sive heating of the end face of the nozzle by providing an air passage which short-circuits from an atomization air passage to the end face of the fuel nozzle and making high pressure atomization air flow a high speed air flow into a low pressure burner. CONSTITUTION:A nozzle core 2 is provided in the central section of a fuel nozzle. Liquid fuel is atomized in a vortex chamber 3 and the atomized fuel is jetted out as a spray from the jet opening 4 of the nozzle. And, round its outer circumference an atomization air flow passage 12 is formed by providing a cone 5. Further, round its outer circumference a revolving cone 7 which is provided on its outer circumference with revolving vanes 10 is provided to form a jet flow passage of a gas fuel 102. And, an atomization air passage hole 14 and a cooling hole 16 for cooling the end face of the nozzle are provided and they are respectively made to go through the end face 8 of the fuel nozzle that is formed by the extensions of the cone 5 and the cone 7 of a revolving member in order to short-circuits the atomization air passage 12 and a burner. By the way 6 is the revolving vanes of the atomization air, 11 is a gas jet opening, and 17 is an opening through which the short-circuited air flows out.

8. 发明专利

JPH024129A SUPPORTING STRUCTURE FOR GAS TURBINE COMBUSTION DEVICE 失效
公开(公告)号：JPH024129A
公开(公告)日：1990-01-09
申请号：JP15416888
申请日：1988-06-22
申请人： HITACHI LTD
发明人： SEGAWA YORIHIDE , TSUKAHARA SATOSHI , KATO FUMIO , KIRIKAMI SEIICHI , ARAI TORU , ISHIBASHI YOJI
IPC分类号： F02C7/20 , F23R3/60
摘要： PURPOSE:To suppress the shaking-rotating vibration of a combustor, and not to restrain the thermal elongation and deformation of components of the combustor by supporting an outlet of a internal drum on an inlet of a tail drum and the inlet of the tail drum on a supporting drum by plate springs of a particular shape that are fitted free to slide in the axial and peripheral directions of the combustor. CONSTITUTION:A combustor consists of an internal drum 1, a tail drum 2, an external drum 3, external frame 4, and a combustion nozzle 5 with a turning device. On each end of wing parts that are extended diagonally on the same side from the middle part and from the both sides of the middle part and are curved, a pressed round parts 11 is formed, and the round part has a sectional shape of convex arc on the opposite sides of the middle part in view of the section perpendicularly intersecting with the center line of the wing part. The plate springs are inserted between the periphery surface of the tail drum inlet 6 and internal surface of the supporting drum 3', and between the periphery surface of internal drum inlet 7 and the internal surface of tail drum inlet, distributing them around peripheries. The plate springs are fitted so as to slide in the axial and peripheral directions against the supporting drum, the tail drum, and the internal drum. Thereby, even though the pressure- vibration of vibrating-combustion in rotation mode acts on the internal drum and the tail drum, those drums rotate shakingly without any restraint because the plate springs are free to deform elastically, causing the vibration to be diminished. The thermal stress is not produced because the elongation of the internal drum and the tail drum in the axial direction is not restrained completely.

9. 发明专利

JPH01125525A GAS TURBINE COMBUSTOR 失效
公开(公告)号：JPH01125525A
公开(公告)日：1989-05-18
申请号：JP24987488
申请日：1988-10-05
申请人： HITACHI LTD
发明人： HAYASHI NORIYUKI , TSUKAHARA SATOSHI , KATO YASUHIRO
IPC分类号： F02C7/18
摘要： PURPOSE:To improve cooling performance of a tail pipe in a combustor provided with an inner pipe and the tail pipe for conducting generated working gas fluid to the turbine side, by providing a through flow path interconnecting the tail pipe belly and back sides near a gas flow outlet of tail pipe so that cooled air flows through said flow path. CONSTITUTION:A combustor has a tail pipe 13 of flow path for introducing high temperature and pressure combustion gas 4 generated in the inner pipe 12 into a turbine 3. Between the tail pipe 13 and the outside casing 14, a wheel chamber 15 is formed as a flow path for converting the direction of air 5 from a compressor 2 to that of flowing into an annular portion between the outer and inner pipes 11, 12. Then, a through flow path 20 for interconnecting the belly and back sides is formed near the outlet of tail pipe 13. Thus, air 5 flowing from the compressor 2 into the wheel chamber 15 flows along the belly side of tail pipe 13, then passes through a through flow pat 20, reaches the back side and then flows between the tail pipe 13 and the casing 14 to flow from the wheel chamber 15 to the annular potion between the outer and inner pipes 11, 12.

10. 发明专利

JPS63309733A GAS TURBINE COMBUSTOR 失效
公开(公告)号：JPS63309733A
公开(公告)日：1988-12-16
申请号：JP14508187
申请日：1987-06-12
申请人： HITACHI LTD
发明人： HAYASHI NORIYUKI , TSUKAHARA SATOSHI , ANZAI SHUNICHI , MORITOMO YOSHIKAZU
IPC分类号： F02C7/18
摘要： PURPOSE:To alleviate pressure loss in a gas turbine combustor in the caption by cooling the turbine nozzle side of a tail cylinder outside which combines a combustor liner with a turbine part by means of impingement cooling effected by a jet striking the surface to be cooled, and also cooling the liner side with the forced convention cooling. CONSTITUTION:A gas turbine combustor has a tail cylinder 2 which combines a combustor liner 1 with a turbine nozzle 101, and a guide wall 7 for covering the tail cylinder 2 is arranged along the outer wall surface of the tail cylinder 2 at a proper distance. In this case, cooling holes 8 and air suction holes 9 respectively consisting of plural rows of a number of small hole are arranged on the guide wall 7. And the liner 1 side of the guide wall 7 is so constructed to be closed that the air 21 flowing from a diffuser 103 into a casing 5 does not flow in the liner 1 through the outside of the guide wall 7, and the cooling air 21 is directed to flow in a gap between the tail cylinder 2 and the guide wall 7 while being separated in the cooling holes 8 and the air suction holes 9. Thereby, the turbine nozzle 101 side of the tail cylinder 2 can be cooled by the impingement cooling with high cooling ability.

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