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公开(公告)号：US20150159555A1
公开(公告)日：2015-06-11
申请号：US14101384
申请日：2013-12-10
CPC分类号： F02C7/224 , F02C7/185 , F05D2260/213 , F05D2260/232 , Y02T50/676
摘要： A gas turbine engine that includes a heat exchanger for heating a fuel gas using compressed air generated by the engine. The heat exchanger is positioned within an outer housing of the engine and receives the fuel gas at a first input prior to the fuel being mixed with a combustion portion of the compressed air and receives a cooling portion of the compressed air at a second input prior to the cooling portion of the compressed gas being sent to cooling flow channels. The heat exchanger also includes a first output that directs the fuel from the heat exchanger to be mixed with the combustion portion of the compressed gas and a second output that directs the cooling portion of the compressed gas to the cooling flow channels.
摘要翻译： 一种燃气涡轮发动机，其包括使用由发动机产生的压缩空气加热燃料气体的热交换器。 热交换器定位在发动机的外壳内并在燃料与压缩空气的燃烧部分混合之前在第一输入处接收燃料气体，并且在第一输入之前在第二输入处接收压缩空气的冷却部分 压缩气体的冷却部分被送到冷却流道。 热交换器还包括第一输出，其将来自热交换器的燃料引导为与压缩气体的燃烧部分混合，以及将压缩气体的冷却部分引导到冷却流道的第二输出。
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公开(公告)号：US09644539B2
公开(公告)日：2017-05-09
申请号：US14077475
申请日：2013-11-12
IPC分类号： F02C7/18
CPC分类号： F02C7/18 , F05D2240/12 , Y02T50/675
摘要： A converging-diverging nozzle that has particular application for providing a cooling air flow to ring segments in a gas turbine engine. The engine includes a turbine section that receives a hot working gas. The turbine section includes at least one row of vanes, at least one row of blades and a plurality of ring segments forming at least one ring. The ring segments and the vanes are mounted to a vane carrier, where the vane carrier includes a cooling flow channel for each of the ring segments that receives an air flow to cool the ring segments. A plug is provided in each channel and has an internal bore shaped to define the converging-diverging nozzle through which the air flows so as to create a supersonic flow that reduces the temperature of the air and thus provides more cooling for the same amount of air flow.
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公开(公告)号：US20150128598A1
公开(公告)日：2015-05-14
申请号：US14077475
申请日：2013-11-12
IPC分类号： F02C7/18
CPC分类号： F02C7/18 , F05D2240/12 , Y02T50/675
摘要： A converging-diverging nozzle that has particular application for providing a cooling air flow to ring segments in a gas turbine engine. The engine includes a turbine section that receives a hot working gas. The turbine section includes at least one row of vanes, at least one row of blades and a plurality of ring segments forming at least one ring. The ring segments and the vanes are mounted to a vane carrier, where the vane carrier includes a cooling flow channel for each of the ring segments that receives an air flow to cool the ring segments. A plug is provided in each channel and has an internal bore shaped to define the converging-diverging nozzle through which the air flows so as to create a supersonic flow that reduces the temperature of the air and thus provides more cooling for the same amount of air flow.
摘要翻译： 一种会聚发散喷嘴，其具有用于向燃气涡轮发动机中的环段提供冷却空气流的特殊应用。 发动机包括接收热工作气体的涡轮部分。 涡轮部分包括至少一排叶片，至少一排叶片和形成至少一个环的多个环形段。 环段和叶片安装到叶片载体上，其中叶片载体包括用于接收空气流以冷却环段的每个环段的冷却流动通道。 在每个通道中设置一个插头，并具有一个内部孔，其形状可以限定会聚的发散喷嘴，空气流过该喷嘴，以产生超音速流动，从而降低空气的温度，从而为相同量的空气提供更多的冷却 流。
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