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公开(公告)号：EP4036375A1
公开(公告)日：2022-08-03
申请号：EP22153535.4
申请日：2022-01-26
发明人： MADONNA, Nicholas J. , ANDERSON, Kristopher K. , ANIELLO, Justin M. , JACQUES, Jeffrey Michael , PREUSS, Daniel P. , RYAN, Christina A. , SHALLCROSS, Melissa
IPC分类号： F01D9/04
摘要： Vane assemblies (400; 500; 600) are described. The vane assemblies include a platform (402; 502; 602), an airfoil (410; 510; 610) extending from the platform, a forward rail (404; 504; 604) extending from the platform and arranged along a forward side of the platform, and an aft rail (406; 506; 606) extending from the platform and arranged along an aft side of the platform. At least one support beam (520; 512; 614a, 614b) is provided extending in a forward-aft direction between the forward rail and the aft rail and separated from the platform by a first distance. The at least one support beam has a thickness (T 1 ) in a radial direction of 40% or less of a total radial extent (T 2 ) from the platform to an outer diameter edge of at least one of the forward rail and the aft rail and the at least one support beam has a thickness (D 1a , D 1b ) in a circumferential direction of 30% or less of a total circumferential extent (D 2 ) of vane assembly.
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公开(公告)号：EP4130433A1
公开(公告)日：2023-02-08
申请号：EP22189285.4
申请日：2022-08-08
发明人： PREUSS, Daniel P. , MONGILLO Jr., Dominic J. , FREDETTE, Jeremy B. , PRENTER, Robin Michael Patrick
IPC分类号： F01D5/18
摘要： A hollow airfoil body (96) includes a baffle (180) that is arranged in the airfoil body (96) that extends in a radial direction (Y) and provides a fluid flow direction (F). The baffle (180) has multiple holes (188a, 188a') that include first and second holes (188a, 188a') that are configured to conduct the cooling airflow (140) in a chordwise direction (Z) toward the trailing edge (122) of the airfoil body (96). The airfoil (100) has a first standoff (190a) that extends from the airfoil body (96) to support the baffle (180). The first axial standoff (190a) has a first length that defines an axial passage including the multiple holes (188a, 188a'). The airfoil (100) includes a second standoff (190b) that has a second length less than the first length. The second standoff (190b) is arranged radially between the first and second holes (188a, 188a'). The first hole (188a) is smaller than the second hole (188a'). The second hole (188a') is downstream from the first hole (188a) relative to the fluid flow direction (F).
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公开(公告)号：EP3730742A1
公开(公告)日：2020-10-28
申请号：EP20169674.7
申请日：2020-04-15
摘要： The present invention relates to a gas turbine engine (20) including a turbine section (28) having a vane assembly (76) including a radially outer platform (168), a radially inner platform (170) and a first airfoil (66) extending between the radially outer platform (168) and the radially inner platform (170). A rail (172) extends radially inward from the inner platform (170). The vane assembly (76) comprises a connected passage (191) mutually formed by and including an airfoil passage (192) within the first airfoil (66), a platform passage (193) located within the inner platform (170) and a rail passage (194) located within the rail (172). This structure allows for a specific control of relative cooling for the different section of the turbine vane and enables to form the connected passage by use of a single core (195).
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公开(公告)号：EP4130432A1
公开(公告)日：2023-02-08
申请号：EP22189275.5
申请日：2022-08-08
摘要： A gas turbine engine includes a compressor section that provides first and second compressor stages that are configured to respectively provide first and second cooling fluids. The first compressor stage has a higher pressure than the second compressor stage. The gas turbine engine further includes a component (150) that has platform (152; 152A; 152B) with an internal cooling passage (168) fed by first and second inlets (190) that respectively receive fluid from the first and second cooling sources (S1, S2). The second inlet is downstream from the first inlet (190).
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