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公开(公告)号：EP1318353B1
公开(公告)日：2008-07-23
申请号：EP02258413.0
申请日：2002-12-05
Applicant: United Technologies Corporation
Inventor： Burd, Steven W. , Graves, Charles B. , Siskind, Kenneth S.
CPC classification number: F23R3/60 , F23M5/02 , F23R3/002 , F23R3/06 , F23R2900/03044
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Patent Agency Ranking
公开(公告)号：EP0927854A2
公开(公告)日：1999-07-07
申请号：EP98310804.4
申请日：1998-12-31
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Segalman, Irving , Hoke, James B. , Siskind, Kenneth S. , Sturgess, Geoffrey J. , Smith, Reid D.C.
CPC classification number: F23C7/004 , F23C6/045 , F23C7/02 , F23C2201/102 , F23D11/107 , F23D2206/10 , F23D2900/11101 , F23R3/06 , Y02E20/344
Abstract: In a method of combusting fuel in the combustion chamber (11) of a gas turbine engine, fuel and a first predetermined amount of air are injected into the combustion chamber to form a fuel-rich mixture, and a second predetermined amount of air is injected downstream, to mix with the mixture and form a lean fuel-air mixture. The combustion chamber (11) has a fuel injector (10) and inlets (17, 19) downstream thereof to allow the air to be injected.
Abstract translation: 在燃气涡轮发动机的燃烧室（11）中燃烧燃料的方法中，将燃料和第一预定量的空气注入燃烧室以形成富燃料混合物，并且注入第二预定量的空气 下游，与混合物混合并形成贫燃料 - 空气混合物。 燃烧室（11）在其下游具有燃料喷射器（10）和入口（17,19），以允许空气被喷射。
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公开(公告)号：EP1318353A3
公开(公告)日：2004-04-14
申请号：EP02258413.0
申请日：2002-12-05
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Burd, Steven W. , Graves, Charles B. , Siskind, Kenneth S.
CPC classification number: F23R3/60 , F23M5/02 , F23R3/002 , F23R3/06 , F23R2900/03044
Abstract: A combustor 10 for a gas turbine engine is provided which includes a plurality of liner segments 12 and a support shell 14. The support shell 14 includes an interior 16 and an exterior 18 surface, a plurality of mounting holes 20, and a plurality of impingement coolant holes 22 extending through the support shell 14. Each liner segment 12 includes a panel 24 and a plurality of mounting studs 32. The panel 24 includes a face surface 34 and a back surface 36, and a plurality of normal or inclined coolant holes 38 extending therethrough. The back surface 36 of the panel 24 has a surface profile for improving the heat transfer properties of a liner segment without substantial increase in pressure drop across the combustor.
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公开(公告)号：EP1318353A2
公开(公告)日：2003-06-11
申请号：EP02258413.0
申请日：2002-12-05
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Burd, Steven W. , Graves, Charles B. , Siskind, Kenneth S.
IPC: F23R3/06
CPC classification number: F23R3/60 , F23M5/02 , F23R3/002 , F23R3/06 , F23R2900/03044
Abstract: A combustor 10 for a gas turbine engine is provided which includes a plurality of liner segments 12 and a support shell 14. The support shell 14 includes an interior 16 and an exterior 18 surface, a plurality of mounting holes 20, and a plurality of impingement coolant holes 22 extending through the support shell 14. Each liner segment 12 includes a panel 24 and a plurality of mounting studs 32. The panel 24 includes a face surface 34 and a back surface 36, and a plurality of normal or inclined coolant holes 38 extending therethrough. The back surface 36 of the panel 24 has a surface profile for improving the heat transfer properties of a liner segment without substantial increase in pressure drop across the combustor.
Abstract translation: 提供了一种用于燃气涡轮发动机的燃烧器10，其包括多个衬垫段12和支撑壳14.支撑壳14包括内部16和外部18表面，多个安装孔20和多个冲击 每个衬垫段12包括一个面板24和多个安装螺柱32.面板24包括一个表面34和一个后表面36以及多个正常或倾斜的冷却剂孔38 延伸穿过。 面板24的后表面36具有用于改善衬套段的传热性能而不会显着增加穿过燃烧器的压降的表面轮廓。
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公开(公告)号：EP0927854B1
公开(公告)日：2006-05-24
申请号：EP98310804.4
申请日：1998-12-31
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Segalman, Irving , Hoke, James B. , Siskind, Kenneth S. , Sturgess, Geoffrey J. , Smith, Reid D.C.
CPC classification number: F23C7/004 , F23C6/045 , F23C7/02 , F23C2201/102 , F23D11/107 , F23D2206/10 , F23D2900/11101 , F23R3/06 , Y02E20/344
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公开(公告)号：EP0927854A3
公开(公告)日：1999-09-29
申请号：EP98310804.4
申请日：1998-12-31
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Segalman, Irving , Hoke, James B. , Siskind, Kenneth S. , Sturgess, Geoffrey J. , Smith, Reid D.C.
CPC classification number: F23C7/004 , F23C6/045 , F23C7/02 , F23C2201/102 , F23D11/107 , F23D2206/10 , F23D2900/11101 , F23R3/06 , Y02E20/344
Abstract: In a method of combusting fuel in the combustion chamber (11) of a gas turbine engine, fuel and a first predetermined amount of air are injected into the combustion chamber to form a fuel-rich mixture, and a second predetermined amount of air is injected downstream, to mix with the mixture and form a lean fuel-air mixture. The combustion chamber (11) has a fuel injector (10) and inlets (17, 19) downstream thereof to allow the air to be injected.
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