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公开(公告)号：EP1033536B1
公开(公告)日：2005-05-18
申请号：EP99943405.3
申请日：1999-09-17
发明人： MANDAI, S., Tak. Res&Dev Cen. Mits. Heavy Ind. Ltd , OHTA, M., Tak. Res&Dev Cen., Mits. Heavy Ind. Ltd. , HARUTA, H., Tak. Mac. Works Mits. Heavy Ind. Ltd. , NISHIDA, K., Tak. Mac. Works Mits. Heavy Ind. Ltd. , AKAMATSU, S., Tak. Mac. Works Mits. Heavy Ind. Ltd , KAMOGAWA, M., Koryo Eng. Co. Ltd.
CPC分类号： F23D11/38 , F23D11/107 , F23D2900/00016 , F23R3/28
摘要： A combustor for gas turbine, wherein a nozzle cap (10) is disposed on the downstream side of a nozzle body (1) of the combustor and its inner surface part (12) is formed in a conical shape gradually larger in diameter toward the downstream side so as to form a fuel jet guide (17) which guides the fuel jet injected from an injection hole (3) provided in the nozzle body at the center part of a downstream side end surface (2) and the fuel injected from the injection hole advances along the jet guide, mixes into a swirl flow (S) in a swirl flow path (9) smoothly without stagnation and burns, thus preventing smoke from producing, and the air introduced, on the upstream side, into a first auxiliary air path (6) between the nozzle body and a partition (5) passes a second auxiliary air path (16) formed between the downstream side end surface (2) of the nozzle body (1) and the upstream side end surface (13) of the nozzle cap, reaches an inlet (19) of the fuel jet guide, and then flows along the fuel jet guide, whereby the nozzle cap is cooled and the fuel injected from the injection hole is prevented from depositing on the nozzle cap.
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公开(公告)号：EP1033536A1
公开(公告)日：2000-09-06
申请号：EP99943405.3
申请日：1999-09-17
发明人： MANDAI, S., Tak. Res&Dev Cen. Mits. Heavy Ind. Ltd , OHTA, M., Tak. Res&Dev Cen., Mits. Heavy Ind. Ltd. , HARUTA, H., Tak. Mac. Works Mits. Heavy Ind. Ltd. , NISHIDA, K., Tak. Mac. Works Mits. Heavy Ind. Ltd. , AKAMATSU, S., Tak. Mac. Works Mits. Heavy Ind. Ltd , KAMOGAWA, M., Koryo Eng. Co. Ltd.
IPC分类号： F23R3/28
CPC分类号： F23D11/38 , F23D11/107 , F23D2900/00016 , F23R3/28
摘要： 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.
摘要翻译： 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着燃料喷射导向装置平滑地延伸，而不残留在旋流通道（9）中的旋流（S），并且不会产生烟雾而燃烧。 被引入第一辅助空气通道（6）的空气通过在喷嘴主体和分隔件（5）的上游位置之间限定的第一辅助空气通道（6）穿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）和喷嘴帽的上游端表面（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盖，并且防止从一个或多个喷嘴孔喷射的燃料粘附到喷嘴帽。
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