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公开(公告)号：JP2003262336A
公开(公告)日：2003-09-19
申请号：JP2002064302
申请日：2002-03-08
Applicant: NAT AEROSPACE LAB
Inventor： HAYASHI SHIGERU , YAMADA SHUJI
Abstract: PROBLEM TO BE SOLVED: To provide a gas turbine combustor capable of obtaining both high combustion efficiency and low NOx discharge concentration over the wide output range by burning lean air-fuel mixture with utilizing high temperature burned gas without using a variable mechanism of air flow for combustion or the like. SOLUTION: The gas turbine combustor 10 is equipped with and a pre- mixture injection pipe 16 introducing an air-fuel mixture into the combustion chamber 11. The mixture from the pre-mixture injection pipe 16 is injected toward the burned gas 19a existing in the downstream of the flame 19 injected from a burner 15 opening the exhaust outlet 15a inside the combustion chamber 11 and mixed with the burned gas 19a. Even if it is mixture out of the lean inflammable limit, an active group in the burned gas 19a is effective for a combustion reaction and the combustion reaction of the mixture can be induced. Since oxygen concentration in the mixture is lower than that in the air and dispersed into space, generation of NOx can be suppressed. COPYRIGHT: (C)2003,JPO
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公开(公告)号：JP2002257334A
公开(公告)日：2002-09-11
申请号：JP2001056218
申请日：2001-03-01
Applicant: NAT AEROSPACE LAB , NIKKISO CO LTD
Inventor： HAYASHI SHIGERU , YAMADA SHUJI , AZUMA MASAICHI , FUKUHARA TOSHIYUKI
Abstract: PROBLEM TO BE SOLVED: To provide a combustion tester having an inexpensive lightweight heat shield exhibiting excellent heat insulation and cooling performance. SOLUTION: The combustion tester comprises a test section casing 4 being fixed with a combustor 5, a heat shield 32 having an annular inner space passing refrigerating medium formed in the test section casing to surround a jet flow of combustion gas 6 from the outlet of the combustor, openings 34 made in the surface of the heat shield and through which cooling medium in the heat shield flows out, and a supply pipe 33 provided for the test section casing in order to supply cooling medium from the outside of the test section casing into the heat shield.
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公开(公告)号：JP2001280605A
公开(公告)日：2001-10-10
申请号：JP2000095978
申请日：2000-03-30
Applicant: NAT AEROSPACE LAB , NORITZ CORP
Inventor： HAYASHI SHIGERU , SHA HAYASHI , WATANABE TOSHIO
Abstract: PROBLEM TO BE SOLVED: To provide combustion equipment which emits less uncombusted components and NOx by improving a combustor which employs a premixing and swirling combustion system. SOLUTION: The combustion equipment has a cylindrical combustion chamber 2 whose one side is open, and in the vicinity of the opening, a step 3 is provided to enlarge the opening. A heat storing member 5 is located at the step 3. The member 5 is heated to red heat by receiving heat and maintains the condition. A mixed gas is injected to the combustion chamber 2 from the tangent direction. Then flames are generated in the combustion chamber 2 to heat the member 5 to red heat. The flames, swirling, reach the vicinity of the opening of the combustion chamber 2 to generate recirculating flow at the step 3. The recirculating flow comes into contact with the member 5 to have the unburnt components contained in the recirculating flow combusted.
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公开(公告)号：JPH11200891A
公开(公告)日：1999-07-27
申请号：JP1317998
申请日：1998-01-08
Applicant: NAT AEROSPACE LAB
Inventor： HAYASHI SHIGERU
Abstract: PROBLEM TO BE SOLVED: To always guarantee stable operation even when an operation condition of pressurized gas fluctuates by storing water unevaporated at water spraying time by a spraying nozzle in the bottom part of a cooler vessel, repeatedly using it, and replenishing water of a quantity taken away outside the vessel as steam. SOLUTION: In a cooler used when exhausting pressurized gas in the atmosphere, and particularly in a cooler in pressurizing combustor testing equipment used to develop a combustor of a jet engine and a gas turbine, a water spraying nozzle 18 is arranged in the upper part of a cooler vessel, and the storage part 21 is formed in the vessel bottom part 21 so that both 18 and 21 are connected by piping 22 in which a force feed pump 17 is interposed. The cooling is performed by contacting spray water from the water spraying nozzle 18 with high temperature gas, and water unevaporated at this time is stored in the storage part 21 to be repeatedly used. Water is replenished by a transporting pump 25 when the fact of a preset level or less is detected by detecting a water surface position 23 of this storage part 21 by a water level gauge 24.
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公开(公告)号：JPH09152105A
公开(公告)日：1997-06-10
申请号：JP33425995
申请日：1995-11-30
Applicant: NAT AEROSPACE LAB
Inventor： HAYASHI SHIGERU , YAMADA SHUJI
Abstract: PROBLEM TO BE SOLVED: To achieve substantially the same NOx exhaust level as in uniform premixing combustion, and solve latent problems such as self-firing and back fire. SOLUTION: Part of a fuel 18 is injected to air on a first air passage 17, at an inlet of which a first air turning unit 15 is provided, with a first fuel nozzle 19 disposed on a burner central axis and remaining part is injected to an air stream flowing through a second air passage 25 where a second turning unit 16 is provided from a fuel injection hole 24 of a second fuel nozzle 23 formed in a wall surface of an outer ring 22. When a fuel flow rate is less or with conditions of low air temperature, the fuel is injected to the first air passage, but in the opposite case, a ratio of fuel injection to the second air passage can be automatically increased. Accordingly, combustion is achieved under the combustion conditions where production of non-combusted components and NOx can be restricted over a wide range the fuel flow rate.
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Patent Agency Ranking
公开(公告)号：JPH0842851A
公开(公告)日：1996-02-16
申请号：JP19615694
申请日：1994-07-29
Applicant: NAT AEROSPACE LAB
Inventor： HAYASHI SHIGERU , YAMADA SHUJI , SHIMODAIRA KAZUO
Abstract: PURPOSE:To provide a dilute premixing combustion gas turbine combustor in which a flow rate change in premixing air can be increased, a fuel/air ratio in a combustion region can satisfactorily be diluted for a wide load variation range, and an exhaust level of NOx can be limited to a very low value irrespective of the load. CONSTITUTION:There is provided a flow passage through which premixing air 14 and dilution air 15 flow, and there is disposed a flow rate distribution mechanism of the premixing air and the dilution air in the flow passage. For the flow rate distribution, it is so constituted that when one is maximum, the other is minimum, and that they are made continuously variable from the maximum to the minimum, and further that a fuel/air ratio of the premixing air is controlled by adjusting the flow rate distribution matching with the flow rate change in the premixing fuel. For the flow rate distribution it is done by an air distributor which is operated with a driver 20, and the location of a valve of the ditributor is adjusted matching with the flow rate change in the premixing fuel.
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公开(公告)号：JP2001336748A
公开(公告)日：2001-12-07
申请号：JP2000155717
申请日：2000-05-26
Applicant: JAPAN SCIENCE & TECH CORP , NAT AEROSPACE LAB
Inventor： HAYASHI SHIGERU
Abstract: PROBLEM TO BE SOLVED: To provide a fuel-staging burner in which a switching mechanism for fuel-supply holes is provided in a fuel nozzle of a single burner for increasing/reducing the number of the injection holes corresponding to a required output, and at the same time the injection space is peripherally and/or radially extended or reduced to control the combustion-air ratio in a wide range of output. SOLUTION: This burner is provided with a nozzle 1, a selector valve 2, and liquid-membrane-forming means 6. The nozzle 1 has fuel-injection holes disposed in axially and peripherally different positions in a combustion duct. The selector valve 2 moves axially relative to the nozzle to open/close the injection holes. The liquid membrane-forming means 6 forms liquid membrane of fuel jetted out of the holes.
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公开(公告)号：JPH11201409A
公开(公告)日：1999-07-30
申请号：JP1317898
申请日：1998-01-08
Applicant: NAT AEROSPACE LAB
Inventor： HAYASHI SHIGERU
Abstract: PROBLEM TO BE SOLVED: To enable mass production by arranging a number of air passages, fuel passages, and swhirl chambers closely and two-dimensionally. SOLUTION: As an example of a rotary burner array which is manufactured by precision casting, a plurality of circular burner arrays are arranged two- dimensionally as a space in a flat plate block. After air 11 advances from a plurality of air inlets 12 at the back of a flat plate block 22 through an air passage 13 which is vertical to a plane of the flat plate block 22, the air 11 enters from a slot section into a swhirl chamber 17 so as to flow into the tangential direction of the swhirl chamber 17 through a passage in the direction of the plane. Fuel 14 is branched by a fuel passage 16 arranged parallel to a flat plate inside a flat plate, distributed toward respective circular burners through a fuel passage which is vertical to the flat table, and blowed out from a fuel supply port into an air current at the upper stream of the slot section. The fuel and the air enter the swhirl chamber 17 from the slot section while being mixed, and blowed out into a combustion chamber from a mixed gas port 21 while whirling along the all surface. A high load burner array capable of mass production can be obtained according to this structure.
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公开(公告)号：JPH06147429A
公开(公告)日：1994-05-27
申请号：JP32749792
申请日：1992-11-13
Applicant: NAT AEROSPACE LAB
Inventor： HAYASHI SHIGERU , YAMADA SHUJI
Abstract: PURPOSE:To provide a burner where a large NOX reduction effect is available even when a higher temperature combustion gas is required compared with a burner outlet gas temperature capable of producing an NOX reduction effect. CONSTITUTION:A large number of flow passages 2 which supply a lean mixture of a fuel gas and an air and other flow passage 6 which allow a fuel gas or a mixture of air to flow therein are laid out in a combustion chamber in such a fashion that they may envelop each other. A fuel gas or a mixture of fuel gas and an air from the passages 6 is designed to flow in.
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公开(公告)号：JP2003214604A
公开(公告)日：2003-07-30
申请号：JP2002011546
申请日：2002-01-21
Applicant: NAT AEROSPACE LAB
Inventor： HAYASHI SHIGERU
Abstract: PROBLEM TO BE SOLVED: To provide a fluid atomizing nozzle which forms a fluid film in a uniform thickness in the circumferential direction as much as possible by using a gas revolving flow, prevents clogging, and makes the size of a splashing droplet further smaller for expediting atomization. SOLUTION: The fluid passing through a fluid passage 14 formed at an outer tube 2, inclined in the diametrical direction and flowing in an annular space 7 is jetted into the annular space 7 having a device turning in the circumferential direction. Air flowing in the annular space 7 through an air passage 10 formed at the outer tube 2, inclined in the same direction as the fluid passage generates the revolving flow Ac in the annular space 7, and works so as to expand the fluid jet over an inner wall 5 of the outer tube 2 to unify the thickness of the fluid film in the peripheral direction. Atomization of the fluid in the fluid film condition is expedited at the time of splashing it from a front end edge 16 of the outer tube 2, and the size of the droplet is made to be further smaller. COPYRIGHT: (C)2003,JPO
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