公开(公告)号：JP2003194337A

公开(公告)日：2003-07-09

申请号：JP2001391789

申请日：2001-12-25

Applicant: NAT AEROSPACE LAB ,  NIIGATA ENGINEERING CO LTD

Inventor： HAYASHI SHIGERU ,  YAMADA SHUJI ,  FUJIWARA HIROSHI

IPC: F23R3/14 ,  F23D14/02 ,  F23R3/30

Abstract: PROBLEM TO BE SOLVED: To provide a preliminary fuel-air mixing tube which reduces backfires without degradation in flame holding performance of the mixture in a swirling motion. SOLUTION: A first swirler 2 for counterclockwise turn is provided on the inner side and a second swirler 3 for clockwise turn is provided on the outer side, with a multiple hole fuel nozzle 1 for gaseous or liquid fuel injection positioned at the center. A premixing tube 4 is a roughly hollow truncated cone (or pyramid) having a virtually circular (or rectangular) cross section, with the cross section growing smaller toward the outlet. The ratio of the area of the nozzle 1 at the injection tip to the area of the outlet is 40%. It is so arranged that 0.02 COPYRIGHT: (C)2003,JPO

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

IPC: F23C99/00 ,  F23D14/02 ,  F23D14/14 ,  F23D14/58 ,  F23C11/00

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.

公开(公告)号：JPH04313608A

公开(公告)日：1992-11-05

申请号：JP10518291

申请日：1991-04-11

Applicant: NAT AEROSPACE LAB

Inventor： HAYASHI SHIGERU ,  YAMADA SHUJI

IPC: F23C99/00 ,  F23D14/02 ,  F23D14/58

Abstract: PURPOSE:To ensure stabilized combustion in the use of a low-NOX burner independent of whether the burner burns a lean mixture or a mixture in the range from lean to rich in the fuel concentration. CONSTITUTION:A short flame 6 is produced from each of many mixture tubes 8, which are provided at an end of a combustion chamber 7 and through which fuel-air mixture flows in, and made to form together with other such flames a thin layer of flames as a whole; in addition, a flow of air 2 is supplied to a part immediately downstream from the layer of flames through air tubes 9 which are disposed in such a manner as to surround and be surrounded mutually with the mixture tubes 8 and which are extended downstream beyond the mixture tubes 8 so that the temperature of the combustion gas directly after the combustion is lowered through its mixing with the supplied air 2 and, as the result, reactions producing NOX are stopped or decelerated, hence a reduction in the NOX content in the emission.

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

IPC: F23R3/18 ,  F23D14/70 ,  F23R3/12 ,  F23R3/14 ,  F23R3/20 ,  F23R3/28 ,  F23R3/32 ,  F23R3/34

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

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

IPC: F23L9/02 ,  F23C99/00 ,  F23M5/08 ,  F23C11/00

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.

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

IPC: F23D14/02 ,  F23C99/00 ,  F23R3/28 ,  F23C11/00

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.

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

IPC: F23R3/06 ,  F23R3/12 ,  F23R3/26 ,  F23R3/30 ,  F23R3/34

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.