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公开(公告)号：US07585152B2
公开(公告)日：2009-09-08
申请号：US10946105
申请日：2004-09-22
CPC分类号： F01D5/18 , F05D2260/201 , F05D2260/221 , F23R3/04 , F23R2900/03041 , F23R2900/03042 , F23R2900/03044
摘要： Cooling jets 1 are provided with a longitudinal aspect 2 greater than width 3. Thus, the coolant flow through the jet 1 is less susceptible to deflection by lateral or cross flows presented to that coolant flow such that cooling by impingement of the coolant flow upon a surface 7 to be cooled is improved. Typically, a plurality of jets 1 are provided in a housing wall 8. These jets 1 will be arranged in an appropriate pattern to achieve cooling by flow impingement upon the surface 7 to be cooled. Possibly, a plurality of jets 1 in an appropriate pattern may be arranged upstream of conventional circular coolant jets in order to provide some protection for those circular coolant jets from lateral or cross flow.
摘要翻译： 冷却喷嘴1设置有大于宽度3的纵向方面2.因此，流过喷嘴1的冷却剂流不易受到呈现给该冷却剂流的横向或横向流动的偏转，使得冷却剂的冷却剂流动到 要冷却的表面7得到改善。 通常，多个喷射器1设置在壳体壁8中。这些喷射器1将被布置成适当的图案，以通过流动冲击来冷却待冷却的表面7上的冷却。 可能地，可以将多个适当图案的喷嘴1布置在传统的圆形冷却剂喷流的上游，以便为这些圆形冷却剂喷嘴提供一些保护以防止横向或横向流动。
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公开(公告)号：US20050074325A1
公开(公告)日：2005-04-07
申请号：US10946105
申请日：2004-09-22
CPC分类号： F01D5/18 , F05D2260/201 , F05D2260/221 , F23R3/04 , F23R2900/03041 , F23R2900/03042 , F23R2900/03044
摘要： Cooling jets 1 are provided with a longitudinal aspect 2 greater than width 3. Thus, the coolant flow through the jet 1 is less susceptible to deflection by lateral or cross flows presented to that coolant flow such that cooling by impingement of the coolant flow upon a surface 7 to be cooled is improved. Typically, a plurality of jets 1 are provided in a housing wall 8. These jets 1 will be arranged in an appropriate pattern to achieve cooling by flow impingement upon the surface 7 to be cooled. Possibly, a plurality of jets 1 in an appropriate pattern may be arranged upstream of conventional circular coolant jets in order to provide some protection for those circular coolant jets from lateral or cross flow.
摘要翻译： 冷却喷嘴1设置有大于宽度3的纵向方面2.因此，流过喷嘴1的冷却剂流不易受到呈现给该冷却剂流的横向或横向流动的偏转，使得冷却剂的冷却剂流动到 要冷却的表面7得到改善。 通常，多个喷射器1设置在壳体壁8中。这些喷射器1将被布置成适当的图案，以通过流动冲击来冷却待冷却的表面7上的冷却。 可能地，可以将多个适当图案的喷嘴1布置在传统的圆形冷却剂喷流的上游，以便为这些圆形冷却剂喷嘴提供一些保护以防止横向或横向流动。
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公开(公告)号：US20060104808A1
公开(公告)日：2006-05-18
申请号：US11252714
申请日：2005-10-19
申请人： Geoffrey Dailey , Guy Snowsill
发明人： Geoffrey Dailey , Guy Snowsill
IPC分类号： F03B11/00
摘要： Efficient cooling of a stage of gas turbine engine turbine blades (36) is achieved by first reducing the pressure of the cooling air after it has been bled from the annulus of the compressor (12) by passing it through a diffuser (30), to a pressure magnitude lower than is required at entry to the turbine blades, then re-pressurising the bled air up to the required entry pressure, by passing it through a radial compressor defined by a cowl (44) positioned in close spaced, co- rotational relationship with the downstream face of the associated turbine disk (34).
摘要翻译： 燃气涡轮发动机涡轮叶片（36）的阶段的有效冷却通过首先在冷却空气从压缩机（12）的环通过其通过扩散器（30）而被排出之后降低其压力 压力值低于在进入涡轮机叶片期间所需的压力，然后通过将排气口定位在紧密间隔开的共同旋转的整流罩（44）所限定的径向压缩机中，将排出的空气重新加压至所需的入口压力 与相关联的涡轮盘（34）的下游面的关系。
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公开(公告)号：US20050244265A1
公开(公告)日：2005-11-03
申请号：US11041269
申请日：2005-01-25
申请人： Geoffrey Dailey , Martin Rose
发明人： Geoffrey Dailey , Martin Rose
CPC分类号： F01D17/167 , F01D5/146 , F01D9/041 , F02C9/22 , Y02T50/673
摘要： Rotary apparatus (17) for a gas turbine engine (10) comprises a rotor assembly (63) and first and second stator assemblies (55, 59) mounted coaxially with respect to each other. The first stator assembly (55) is upstream of the second stator assembly (59), and the second stator assembly (59) is upstream of the rotor assembly (63). The rotor assembly (63) comprises an annular array (64) of rotor blades (66), and each stator assembly (55, 59) comprises an annular array (56, 60) of stator vanes (58, 62). Each vane (58, 62) has a leading edge and a trailing edge. The stator assemblies (55, 59) are circumferentially translatable relative to each other between a first condition in which each of the vanes (62) of the second stator assembly (59) is substantially aerodynamically aligned with a respective one of the vanes (58) of the first stator assembly (55), and a second condition in which the vanes (58, 62) of the first and second stator assemblies (55, 59) are out of aerodynamic alignment with each other. In the first condition, at least a part of each vane (62) of the second stator assembly (59) extends beyond the trailing edge of the respective vane (58) of the first stator assembly (55).
摘要翻译： 用于燃气涡轮发动机（10）的旋转装置（17）包括转子组件（63）和相对于彼此同轴安装的第一和第二定子组件（55,59）。 第一定子组件（55）在第二定子组件（59）的上游，并且第二定子组件（59）在转子组件（63）的上游。 转子组件（63）包括转子叶片（66）的环形阵列（64），并且每个定子组件（55,59）包括定子叶片（58,62）的环形阵列（56,60）。 每个叶片（58,62）具有前缘和后缘。 定子组件（55,59）在其中第二定子组件（59）的每个叶片（62）与相应的一个叶片（58）基本上空气动力学对准的第一状态之间相对于彼此沿周向平移， 和第一和第二定子组件（55,59）的叶片（58,62）彼此脱离气动对准的第二状态。 在第一条件下，第二定子组件（59）的每个叶片（62）的至少一部分延伸超过第一定子组件（55）的相应叶片（58）的后缘。
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