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公开(公告)号：EP4442962A1
公开(公告)日：2024-10-09
申请号：EP24161760.4
申请日：2024-03-06
申请人： RTX Corporation
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F01D5/187 , F05D2260/20120130101 , F05D2260/20220130101 , F05D2230/21120130101 , F05D2230/2120130101 , F05D2220/3220130101
摘要： A turbine engine airfoil element has an airfoil having: a pressure side (132) and a suction side (134); and a plurality of spanwise passageway legs (210, 212, 214, 216, 218, 220, 222, 224, 226, 310, 312, 314, 316, 318, 320, 322, 324, 326, 328, 330, 332). The passageway legs (210...332) include: a leading edge impingement cavity (210); and a plurality of main body feed passageway legs (212, 214, 216, 218, 220, 222, 224, 226) along a camber line (190). A wall separates the leading edge impingement cavity (210) from a leading one of the main body feed passageway legs (212), the wall having a suction side section and a pressure side section joining at a junction (364), the junction forming a vertex of an angle (θw) of transverse cross-section of the wall; and a plurality of impingement feed holes through the wall. The plurality of impingement feed holes are larger thickness-wise than span-wise.
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公开(公告)号：EP4428338A2
公开(公告)日：2024-09-11
申请号：EP24161733.1
申请日：2024-03-06
申请人： RTX Corporation
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F01D5/187 , F05D2260/20220130101 , F05D2260/20120130101 , F05D2220/3220130101 , F05D2230/2120130101 , F05D2230/21120130101
摘要： A turbine engine airfoil element has: a plurality of spanwise main body passageways (210, 212, 214, 216, 218, 220, 222, 224, 226, 228) along a camber line (190); and a plurality of spanwise skin passageways (310, 312, 314, 316, 318, 320) along the pressure side (132). The spanwise skin passageways (310, 312, 314, 316, 318, 320) include: first skin passageways (310, 314, 320) each having a plurality of film cooling outlets (339) to the pressure side (132); and second skin passageways (316, 318, 320) each lacking film cooling outlets (339) to the pressure side (132). Linking passageways (334) extend between the first skin passageways (310, 314, 320) and the second skin passageways (316, 318, 320). The first skin passageways (310, 314, 320) and second skin passageways (316, 318, 320) are directly fed from one or more inlets of the airfoil element.
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公开(公告)号：EP4417790A1
公开(公告)日：2024-08-21
申请号：EP24158469.7
申请日：2024-02-19
申请人： RTX Corporation
IPC分类号： F01D5/18
摘要： A turbine blade (74) for a gas turbine engine, including: an airfoil (80), the having a leading edge (82), a pressure side (84), a suction side (86) and a trailing edge (88); a plurality of internal cooling cavities including a leading edge cavity (90), a leading edge feed passage (92), pressure side cooling passages (94), suction side cooling passages (96) and main body cavities (98); the leading edge cavity (90) extending towards the suction side (86); a first crossover row of cooling passages (100) providing fluid communication between the leading edge cavity (90) and the leading edge feed passage (92); and a second crossover row of cooling passages (102) providing fluid communication between the leading edge cavity (90) and the leading edge feed passage (92), a centerline (144) of the first crossover row of cooling passages (100) is located closer to the pressure side (84) than a centerline (136) of the second crossover row of cooling passages (102) and the centerline (136) of the second crossover row of cooling passages (102) is located closer to the suction side (86) than the centerline (144) of the first crossover row of cooling passages (100), and wherein the second crossover row of cooling passages (102) are radially staggered relative to the first crossover row of cooling passages (100).
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公开(公告)号：EP4317650A1
公开(公告)日：2024-02-07
申请号：EP23189305.8
申请日：2023-08-02
申请人： RTX Corporation
摘要： A gas turbine engine component (100; 140; 150) includes a body having an internal cooling passage (106) with opposed walls (108, 110) and an array of heat transfer members (120, 126, 132; 200; 225; 250; 270; 290; 300; 308; 314) attached to at least one of the opposed walls 9108, 110) each with at least one fillet. There is an airflow direction through the cooling passage (106) such that the heat transfer members (120...314) have a leading edge and a trailing edge. The at least one fillets have a leading edge portion and a trailing edge portion, said leading edge portion being asymmetric relative to said trailing edge portion to control an air flow direction towards downstream ones of said heat transfer members (120... 314) in said array.
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