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1. 发明公开

EP2179143A2 SPALTKÜHLUNG ZWISCHEN BRENNKAMMERWAND UND TURBINENWAND EINER GASTURBINENANLAGE 有权转让
标题翻译： GAP之间的冷却燃气轮机墙壁和墙上的燃气涡轮机系统
公开(公告)号：EP2179143A2
公开(公告)日：2010-04-28
申请号：EP08786927.7
申请日：2008-08-06
申请人： ALSTOM Technology Ltd
发明人： STEIGER, Ulrich , HOFMANN, Willy Heinz
IPC分类号： F01D9/02 , F01D5/14 , F01D25/12
CPC分类号： F01D5/143 , F01D11/001
摘要： The invention relates to a gas turbine installation (1) in particular for a power station, comprising a combustion chamber (2) which radially bounds a combustion chamber gas path (9) at least in an annular outlet area (6) with a chamber inner wall (7) and with a chamber outer wall (8), a turbine (3), which radially bounds a turbine gas path (13) in a stationary, annular inlet area (10) with a turbine inner wall (11) and with a turbine outer wall (12), a gap (4; 16, 17) which is provided radially on the inside and/or radially on the outside axially between the combustion chamber (2) and the turbine (3) and at which the inner and/or outer chamber wall (7, 8) and the inner and/or outer turbine wall (11, 12) end/ends, and a cooling gas supply (5) which introduces a cooling gas through the gap into the turbine gas path (13) and/or into the combustion chamber gas path (9). An end section (21, 22, 23, 24), which is adjacent to the gap of the respective turbine wall (11, 12) and/or of the respective chamber wall (7, 8) is shaped radially on the inside and/or radially on the outside such that positive steps (a, c), in the case of which the respective downstream wall projects with respect to the respective upstream wall (7, 8) radially into the respective gas path (9, 13), and negative steps (b, d), in the case of which the respective upstream wall projects radially into the respective gas path (9, 13) with respect to the respective downstream wall, alternates in the circumferential direction on the gap.

2. 发明公开

EP2268900A1 SCHAUFEL FÜR EINE ROTIERENDE THERMISCHE MASCHINE 审中-公开
标题翻译： SCOOP用于旋转热合机
公开(公告)号：EP2268900A1
公开(公告)日：2011-01-05
申请号：EP09724433.9
申请日：2009-03-04
申请人： Alstom Technology Ltd
发明人： HOFMANN, Willy Heinz , HUBER, Michael
IPC分类号： F01D5/14
CPC分类号： F01D5/141 , F01D9/02 , F05D2240/122 , F05D2240/304 , F05D2250/70
摘要： The invention relates to a blade (20) for a rotating thermal engine, in particular a guide vane for the low-pressure turbine of a gas turbine with sequential combustion. Said blade comprises a vane (22) that extends essentially in the radial direction and around which a working medium flows, and that is defined in the direction of flow by a front edge (27) and a rear edge (28). The competitive flow techniques and constructive requirements of the blade, in the event of a steep inclination of the flow, can be fulfilled as the vane (22) is formed such that the angle (α) that forms the flow lines (26) with the rear edge (28) of the vane (22) deviates at a right angle in a defined periphery.

3. 发明公开

EP2831383A1 EXHAUST DIFFUSER FOR A GAS TURBINE 有权转让
标题翻译： ABGASVERTEILERFÜREINE GASTURBINE
公开(公告)号：EP2831383A1
公开(公告)日：2015-02-04
申请号：EP13712242.0
申请日：2013-03-25
申请人： ALSTOM Technology Ltd
发明人： HOFMANN, Willy Heinz , SCHAEFER, Philipp
IPC分类号： F01D25/30
CPC分类号： F01D25/30 , F01D9/02 , F01D25/28 , F02C7/20 , F02K1/04 , F05B2250/711 , F05B2250/712 , F05B2250/713 , F05D2240/90
摘要： An exhaust diffuser for a gas turbine comprises an annular duct (1). A row of struts (6) is arranged in the duct. In a region downstream of the trailing edges (TE) of the struts (6), the cross-sectional area of the duct decreases to a local minimum (M) and then increases again towards the outlet end (3) of the duct. Thereby the gas flow is locally accelerated downstream of the struts. This stabilizes the boundary layer of the flow in this region and leads to a marked increase in pressure recovery for a wide range of operating conditions.
摘要翻译：燃气轮机的排气扩散器包括环形管道（1）。一排支柱（6）布置在管道中。在支柱（6）的后缘（TE）下游的区域中，管道的横截面面积减小到局部最小值（M），然后再次朝管道的出口端（3）增加。因此，气流在支柱的下游局部加速。这使得该区域中的流动的边界层稳定，并且在宽范围的操作条件下导致压力恢复的显着增加。

4. 发明公开

EP2260180A2 LEITSCHAUFEL FÜR EINE GASTURBINE 有权转让
标题翻译： LEITSCHAUFELFÜREINE GASTURBINE
公开(公告)号：EP2260180A2
公开(公告)日：2010-12-15
申请号：EP09726037.6
申请日：2009-03-05
申请人： ALSTOM Technology Ltd
发明人： HOFMANN, Willy Heinz , DÜCKERSHOFF, Roland , WARDLE, Brian, Kenneth
IPC分类号： F01D5/14 , F01D5/18 , F01D9/04
CPC分类号： F01D5/147 , F01D5/187 , F01D9/041 , F05D2220/3215 , F05D2230/21 , F05D2240/301 , F05D2250/185 , F05D2260/22141
摘要： The invention relates to a guide vane (20) for a gas turbine (10), in particular for a low-pressure turbine (18) of a gas turbine (10) with sequential combustion, comprising a vane (22) that extends in the radial direction between an inner platform (23) and an outer platform (21), extending in the inner cooling channel thereof (30, 31, 32), through which a cooling medium, in particular cooling air, for cooling the guide vane (20) can flow. In said type of guide vane, the desired service life and cooling, in relation to the used casting process is achieved such that the vane (22) comprises a transversal surface of the blade material in the radial direction, that varies about the height (h) of the vane (22).
摘要翻译：本发明涉及一种用于燃气涡轮机（10）的导流叶片（20），特别是用于具有顺序燃烧的燃气涡轮机（10）的低压涡轮机（18），其包括叶片（22）在内部平台（23）和外部平台（21）之间沿径向延伸，在其内部冷却通道（30,31,32）中延伸，冷却介质特别是冷却空气通过该冷却介质冷却导流叶片）可以流动。在所述类型的导向叶片中，相对于所使用的铸造过程实现期望的使用寿命和冷却，使得叶片（22）包括叶片材料沿径向方向的横向表面，该横向表面沿高度（h ）的叶片（22）。

5. 发明授权

EP2179143B1 SPALTKÜHLUNG ZWISCHEN BRENNKAMMERWAND UND TURBINENWAND EINER GASTURBINENANLAGE 有权转让
标题翻译： GAP之间的冷却燃气轮机墙壁和墙上的燃气涡轮机系统
公开(公告)号：EP2179143B1
公开(公告)日：2011-01-26
申请号：EP08786927.7
申请日：2008-08-06
申请人： ALSTOM Technology Ltd
发明人： STEIGER, Ulrich , HOFMANN, Willy Heinz
IPC分类号： F01D9/02 , F01D5/14 , F01D25/12
CPC分类号： F01D5/143 , F01D11/001
摘要： The invention relates to a gas turbine installation (1) in particular for a power station, comprising a combustion chamber (2) which radially bounds a combustion chamber gas path (9) at least in an annular outlet area (6) with a chamber inner wall (7) and with a chamber outer wall (8), a turbine (3), which radially bounds a turbine gas path (13) in a stationary, annular inlet area (10) with a turbine inner wall (11) and with a turbine outer wall (12), a gap (4; 16, 17) which is provided radially on the inside and/or radially on the outside axially between the combustion chamber (2) and the turbine (3) and at which the inner and/or outer chamber wall (7, 8) and the inner and/or outer turbine wall (11, 12) end/ends, and a cooling gas supply (5) which introduces a cooling gas through the gap into the turbine gas path (13) and/or into the combustion chamber gas path (9). An end section (21, 22, 23, 24), which is adjacent to the gap of the respective turbine wall (11, 12) and/or of the respective chamber wall (7, 8) is shaped radially on the inside and/or radially on the outside such that positive steps (a, c), in the case of which the respective downstream wall projects with respect to the respective upstream wall (7, 8) radially into the respective gas path (9, 13), and negative steps (b, d), in the case of which the respective upstream wall projects radially into the respective gas path (9, 13) with respect to the respective downstream wall, alternates in the circumferential direction on the gap.

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