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1. 发明公开

EP4269754A3 AIRFOIL WITH RIBS DEFINING SHAPED COOLING CHANNEL 审中-实审
公开(公告)号：EP4269754A3
公开(公告)日：2024-04-10
申请号：EP23196960.1
申请日：2020-11-12
申请人： RTX Corporation
发明人： SPANGLER, Brandon W. , PACK, David R.
IPC分类号： F01D5/14 , F01D5/18 , F01D9/06
摘要： An airfoil (60) includes an airfoil wall (62) that defines a leading end (62a), a trailing end (62b), a pressure side (62c), a suction side (62d), and a mean line (M). First and second ribs (64) each connect the pressure side (62c) and the suction side (62d). Each of the first and second ribs (64) define a tube portion (66) that circumscribes a rib passage (68), and first and second connector arms (1, 2, 5, 6, 3, 4, 7, 8) that solely join the tube portion (66) to, respectively, the pressure side (62c) and the suction side (62d). The first rib (64), the second rib (64), and the airfoil wall (62) bound a continuous cooling channel (72) there between. The continuous cooling channel (72) has a pressure side portion (72a) to the pressure side of the mean line (M) and a suction side portion (72b) to the suction side of the mean line (M). The pressure side portion (72a) and the suction side portion (72b) each have a cross-sectioned shape that is an L-shape.

2. 发明公开

EP4343116A2 AIRFOILS WITH LOBED COOLING CAVITIES 审中-实审
公开(公告)号：EP4343116A2
公开(公告)日：2024-03-27
申请号：EP23199539.0
申请日：2023-09-25
申请人： RTX Corporation
发明人： SPANGLER, Brandon W. , PACK, David R.
IPC分类号： F01D5/14 , F01D5/18 , F01D9/06
摘要： A turbine engine airfoil element has a plurality of main body passageways (210, 212, 214, 216, 218, 220) along a camber line (190) and having two or more chordwise distributed protuberant portions (240, 242, 246, 248, 22, 254, 256) with necks (244, 250, 258, 260) between the protuberant portions (240...256). A plurality of skin passageways (310, 312, 314, 316, 318, 320; 322, 324, 326, 328, 330, 332) include: at least one first skin passageway (312, 316; 324, 328) each nested between a first of the pressure side (132) and the suction side (134) and two adjacent main body passageways (212, 214, 216); and a plurality of second skin passageways (310, 314, 318, 320; 322, 326, 330, 332) each nested between first of the pressure side (132) and the suction side (134) and two said protuberant portions (240...256) of a corresponding main body passageway (212, 214, 216).

3. 发明公开

EP4230842A3 AIRFOIL WITH RIB HAVING CONNECTOR ARMS 审中-实审转让
公开(公告)号：EP4230842A3
公开(公告)日：2023-12-13
申请号：EP23186058.6
申请日：2020-08-18
申请人： RTX Corporation
发明人： SPANGLER, Brandon W. , PACK, David R.
IPC分类号： F01D5/14 , F01D5/18
摘要： An airfoil (60) includes an airfoil wall (62) that defines a leading end (62a), a trailing end (62b), and first and second sides (62c, 62d) joining the leading end (62a) and the trailing end (62b), the first and second sides (62c, 62d) spanning in a radial direction; and first, second, and third ribs (164a, 164b, 164c) connecting the first and second sides (62c, 62d) of the airfoil wall (62). Each of the first, second, and third ribs (164a, 164b, 164c) define a tube portion (66) circumscribing a rib passage (68), and first and second connector arms (70a, 70b) solely joining the tube portion (66) to, respectively, the first and second sides (62c, 62d) of the airfoil wall (62). The first rib (164a) and the airfoil wall (62) bound a first cooling channel (172a) there between that is flow isolated from the rib passage (68) of the first rib (164a). The first rib (164a), the second rib (164b), and the airfoil wall (62) bound a second cooling channel (172b) there between, the first rib (164a) having a first cooling aperture (74) fluidly connecting the rib passage (68) and the second cooling channel (172b). The second rib (164b), the third rib (164c), and the airfoil wall (62) bound a third cooling channel (172c) there between, the second rib (164b) having a second cooling aperture (74) fluidly connecting the rib passage (68) of the second rib (164b) and the third cooling channel (172c). The second cooling channel (172b) and the third cooling channel (172c) are connected in a serpentine flow pattern.

4. 发明公开

EP4343116A3 AIRFOILS WITH LOBED COOLING CAVITIES 审中-实审
公开(公告)号：EP4343116A3
公开(公告)日：2024-04-17
申请号：EP23199539.0
申请日：2023-09-25
申请人： RTX Corporation
发明人： SPANGLER, Brandon W. , PACK, David R.
IPC分类号： F01D5/14 , F01D5/18 , F01D9/06
CPC分类号： F01D5/187 , F01D9/065 , F01D5/147 , F05D2230/21120130101 , F05D2240/30120130101 , F05D2250/1120130101 , F05D2260/20220130101
摘要： A turbine engine airfoil element has a plurality of main body passageways (210, 212, 214, 216, 218, 220) along a camber line (190) and having two or more chordwise distributed protuberant portions (240, 242, 246, 248, 22, 254, 256) with necks (244, 250, 258, 260) between the protuberant portions (240...256). A plurality of skin passageways (310, 312, 314, 316, 318, 320; 322, 324, 326, 328, 330, 332) include: at least one first skin passageway (312, 316; 324, 328) each nested between a first of the pressure side (132) and the suction side (134) and two adjacent main body passageways (212, 214, 216); and a plurality of second skin passageways (310, 314, 318, 320; 322, 326, 330, 332) each nested between first of the pressure side (132) and the suction side (134) and two said protuberant portions (240...256) of a corresponding main body passageway (212, 214, 216).

5. 发明公开

EP4269754A2 AIRFOIL WITH RIBS DEFINING SHAPED COOLING CHANNEL 审中-实审
公开(公告)号：EP4269754A2
公开(公告)日：2023-11-01
申请号：EP23196960.1
申请日：2020-11-12
申请人： RTX Corporation
发明人： SPANGLER, Brandon W. , PACK, David R.
IPC分类号： F01D9/06
摘要： An airfoil (60) includes an airfoil wall (62) that defines a leading end (62a), a trailing end (62b), a pressure side (62c), a suction side (62d), and a mean line (M). First and second ribs (64) each connect the pressure side (62c) and the suction side (62d). Each of the first and second ribs (64) define a tube portion (66) that circumscribes a rib passage (68), and first and second connector arms (1, 2, 5, 6, 3, 4, 7, 8) that solely join the tube portion (66) to, respectively, the pressure side (62c) and the suction side (62d). The first rib (64), the second rib (64), and the airfoil wall (62) bound a continuous cooling channel (72) there between. The continuous cooling channel (72) has a pressure side portion (72a) to the pressure side of the mean line (M) and a suction side portion (72b) to the suction side of the mean line (M). The pressure side portion (72a) and the suction side portion (72b) each have a cross-sectioned shape that is an L-shape.

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