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1. 发明公开

US20240125272A1 COOLING FEATURES FOR A COMPONENT OF A GAS TURBINE ENGINE 审中-公开
公开(公告)号：US20240125272A1
公开(公告)日：2024-04-18
申请号：US18379958
申请日：2023-10-13
申请人： RTX Corporation
发明人： Billie R. Maldonado , Thurman C. Dabbs , James R. Plante , Paul M. Lutjen , Dmitriy A. Romanov , Morely S. Sherman , Nolan Frederic Quinn , Mary E.M. Hiller , Jon Moore , John R. Paulus
IPC分类号： F02C7/18 , F01D5/18 , F01D25/12
CPC分类号： F02C7/18 , F01D5/187 , F01D25/12 , F05D2250/70 , F05D2260/232
摘要： A component for a gas turbine engine, including: at least one internal cavity extending through the component, the internal cavity having at least one inlet opening and at least one outlet opening each being in fluid communication with the at least one internal cavity; a plurality of cooling features extending from a surface of the at least one internal cavity, the plurality of cooling features are formed in accordance with at least one of the following groups: i) a plurality of airfoil shaped features that extend upwardly from the surface of the at least one internal cavity and a plurality of wedge shaped features each having a triangular base that has an upstream portion and a downstream portion, the upstream portion extending further from the surface than the downstream portion; ii) a plurality features having a curved or “J” shaped base that extends upwardly from the surface, a plurality features having a double curved or symmetrically “J” shaped base that extends upwardly from the surface, and a plurality features having a base that extends upwardly from the surface with a curved portion that defines an opening therethrough; iii) a first plurality of pins with a plurality of grooves that are formed into a peripheral surface of each of the first plurality of pins and a second plurality of pins with a plurality of grooves that are formed into a peripheral surface of each of the second plurality of pins the plurality of grooves formed in the peripheral surface of each of the second plurality of pins are configured such that “V” shapes or inverted “V” shapes are formed in the peripheral surface of each of the second plurality of pins; and iv) a plurality of chevron shaped trip strips that are located in a channel, the plurality of chevron shaped trip strips are spaced from each other such that a “U” shaped passage is formed therebetween and each chevron shaped trip strip has a top portion that curls inwardly towards the channel and a plurality of pairs of features that each extend from a surface of another channel towards each other where a gap is located between distal ends of the plurality of pairs of features.

2. 发明公开

US20240110488A1 BLADE OUTER AIR SEAL WITH COMPLIANT SEAL 审中-公开
公开(公告)号：US20240110488A1
公开(公告)日：2024-04-04
申请号：US18456787
申请日：2023-08-28
申请人： RTX CORPORATION
发明人： Paul M. Lutjen , Daniel S. Rogers , Timothy J. Harding , James E. Weisheit , Morely S. Sherman , Mikayla M. Rogers , Marshall F. Thayer , Joseph Micucci
IPC分类号： F01D11/16
CPC分类号： F01D11/16 , F05D2240/55 , F05D2260/38 , F05D2300/6033
摘要： A gas turbine engine includes a turbine section that has a ceramic matrix composite body that defines a core gaspath side that a row of blades, a forward end, an aft end, and circumferential sides. The forward end abuts at least one vane of a first row of vanes, and the aft end including a seal channel. A compliant seal is disposed in the seal channel and seals against at least one vane of a second row of vanes.

3. 发明公开

US20240110487A1 BLADE OUTER AIR SEAL WITH RETAINER RING 审中-公开
公开(公告)号：US20240110487A1
公开(公告)日：2024-04-04
申请号：US18477912
申请日：2023-09-29
申请人： RTX CORPORATION
发明人： Daniel S. Rogers , James E. Weisheit , Morely S. Sherman , Mikayla M. Rogers , Timothy J. Harding , Marshall F. Thayer , Joseph Micucci
IPC分类号： F01D11/08 , F01D9/04
CPC分类号： F01D11/08 , F01D9/04 , F05D2300/6033
摘要： A gas turbine engine includes a turbine section that has a retainer ring, a first vane that bears against the retainer ring to prevent movement of the first vane in a first axial direction, a second vane axially spaced from the first vane, and a blade axially between the first vane and the second vane. A blade outer air seal is situated radially outwardly of the blade. The blade outer air seal includes a ceramic matrix composite body that defines a core gaspath side that faces the blade, a forward end, an aft end, and circumferential sides. There is a spring seal at the aft end of the blade outer air seal that seals against the second vane. The spring seal provides a preload that biases the blade outer air seal against the first vane and thereby biases the first vane against the retainer ring.

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