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    • 7. 发明授权
    • Gas turbine combustor having multiple independently operable burners and staging method thereof
    • 具有多个可独立操作的燃烧器的燃气轮机燃烧器及其分级方法
    • US07797942B2
    • 2010-09-21
    • US11266202
    • 2005-11-04
    • Toshihiko SaitohMasataka OhtaShinji AkamatsuMasakazu Nose
    • Toshihiko SaitohMasataka OhtaShinji AkamatsuMasakazu Nose
    • F02C1/00F02G3/00
    • F23R3/343F23R3/286
    • In a combustor of a gas turbine which has a pilot nozzle being installed to the center of the axis of a combustor basket and a plurality of main nozzles being installed to the vicinity of the pilot nozzle and provided with a premixing tool on the outer circumference thereof, wherein, fuel being injected as air-fuel pre-mixture from the main nozzle into the interior of a transition piece forming a combustion chamber downstream of the combustor basket is ignited by diffusion flame being generated by the pilot nozzle in the transition piece so as to generate a premixed flame in the transition piece, wherein combustion is performed by a part of the plurality of main nozzles from start-up until a predetermined load rate and then performed by adding the remaining portion of the plurality of main nozzles when the predetermined load rate is exceeded.
    • 在燃气轮机的燃烧器中,具有安装在燃烧器筐的轴心的中心的先导喷嘴,并且多个主喷嘴安装在导向喷嘴附近,并且在其外周上设置有预混合工具 其特征在于,从所述主喷嘴向所述燃烧器筐下游形成燃烧室的过渡部件的内部喷射的燃料被喷射,所述扩散火焰由所述过渡部件中的先导喷嘴产生, 以在过渡件中产生预混合的火焰,其中燃料由多个主喷嘴的一部分从起动直到预定的负载率进行,然后通过在预定的负载下加入多个主喷嘴的剩余部分 率超过。
    • 8. 发明授权
    • Gas turbine fuel injector with unequal fuel distribution
    • 具有不均等燃料分配的燃气轮机燃油喷射器
    • US06460339B2
    • 2002-10-08
    • US09828138
    • 2001-04-09
    • Koichi NishidaKatsunori TanakaShigemi MandaiYutaka KawataMasataka Ohta
    • Koichi NishidaKatsunori TanakaShigemi MandaiYutaka KawataMasataka Ohta
    • F02G300
    • F23R3/343F23R3/286
    • A gas turbine combustor improves the fuel distribution from a main fuel nozzle, suppressing fluctuations of internal pressure and elevation of inner tube metal temperature, and enhancing the combustion stability and durability of the combustor. The gas turbine combustor is a multi-nozzle type premixing combustor with a nozzle outer tube (7) for forming and injecting a premixed gas of main fuel and combustion air divided and disposed in plural sections around a cone (4) for forming a diffusion flame by reaction between pilot fuel and combustion air disposed in a center of a section of a combustor inner tube (1). Nozzle holes (5a) of a main fuel nozzle (5) are formed in three positions at equal intervals on the nozzle main body wall, and one of them is disposed at the outer periphery of the combustor inner tube (1) on a diametral line linking between the center of the combustor inner tube (1) and the center of the main fuel nozzle (5), whereby the fuel distribution to the outer periphery is decreased.
    • 燃气轮机燃烧器改善来自主燃料喷嘴的燃料分布,抑制内部压力的波动和内管金属温度升高,提高燃烧器的燃烧稳定性和耐久性。 燃气轮机燃烧器是具有喷嘴外管(7)的喷嘴外管(7)的多喷嘴型预混合燃烧器,用于形成并喷射主燃料和燃烧空气的预混合气体,燃烧空气以形成扩散火焰的锥体(4)为中心分成多个部分 通过引燃燃料与设置在燃烧器内管(1)的一部分的中心的燃烧空气之间的反应。 主燃料喷嘴(5)的喷嘴孔(5a)以等间隔在喷嘴主体壁上形成三个位置,其中一个位于燃烧器内管(1)的外径上, 在燃烧器内管(1)的中心与主燃料喷嘴(5)的中心之间连接,从而减少了向外周的燃料分配。
    • 9. 发明授权
    • Gas turbine combustor with fuel and air swirler
    • 燃气涡轮燃烧器与燃料和空气旋流器
    • US06301900B1
    • 2001-10-16
    • US09554447
    • 2000-07-06
    • Shigemi MandaiMasataka OhtaHideki HarutaKoichi NishidaShinji AkamatsuMasahiro Kamogawa
    • Shigemi MandaiMasataka OhtaHideki HarutaKoichi NishidaShinji AkamatsuMasahiro Kamogawa
    • F23R314
    • F23D11/38F23D11/107F23D2900/00016F23R3/28
    • A nozzle cap (10) is disposed downstream of a nozzle body (1) of a combustor for a gas turbine, an inner surface part (12) of which is of a conical shape diverging downstream to define a fuel-jet guide (17) for guiding fuel jet ejected from one or more nozzle holes (3) provided at the center of a downstream end surface of the nozzle body. Fuel ejected from the one or more nozzle holes smoothly runs along the fuel-jet guide without remaining there to join with a swirl stream (S) in a swirl path (9), and to burn without generating smoke. Air introduced into a first auxiliary air path (6) defined between the nozzle body and a partition (5) at a position upstream thereof passes through a second auxiliary air path (16) defined between a downstream end surface (2) of the nozzle body (1) and an upstream end surface (13) of the nozzle cap and reaches an entrance (19) of the fuel-jet guide. The air then flows along the fuel-jet guide to cool the nozzle cap and prevent the fuel ejected from the one or more nozzle holes from sticking to the nozzle cap.
    • 喷嘴盖(10)设置在用于燃气轮机的燃烧器的喷嘴主体(1)的下游,其内表面部分(12)具有向下游扩散的锥形形状,以限定燃料喷射引导件(17) 用于引导从设置在喷嘴体的下游端面的中心的一个或多个喷嘴孔(3)喷出的燃料喷射。 从一个或多个喷嘴孔喷出的燃料沿燃料喷射导向装置平滑地延伸,而不残留在漩涡路径(9)中的旋流(S),并且燃烧而不产生烟雾。 被引入第一辅助空气通道(6)中的空气通道(6),其限定在喷嘴主体和分隔件(5)之间的位于其上游的位置处,通过限定在喷嘴体的下游端面(2)之间的第二辅助空气通道 (1)和喷嘴盖的上游端表面(13)到达燃料喷射引导件的入口(19)。 然后空气沿着燃料喷射引导件流动以冷却喷嘴帽,并且防止从一个或多个喷嘴孔喷出的燃料粘附到喷嘴帽。