公开(公告)号：US20210324741A1

公开(公告)日：2021-10-21

申请号：US16850593

申请日：2020-04-16

Applicant: Raytheon Technologies Corporation

Inventor： Brandon W. Spangler

IPC: F01D5/14

Abstract: An airfoil includes an airfoil wall that defines a leading end, a trailing end, a first side wall, and a second side wall. A rib connects the first and second side walls of the airfoil wall. The rib includes first and second unbranched arms that initiate at the second side wall and extend there from to meet at a node. A third unbranched arm initiates at the first side wall. The third unbranched arm extends perpendicularly there from and connects at either the node, the first unbranched arm, or the unbranched second arm.

公开(公告)号：US20240301799A1

公开(公告)日：2024-09-12

申请号：US18118365

申请日：2023-03-07

Applicant: Raytheon Technologies Corporation

Inventor： Brandon W. Spangler

IPC: F01D5/20 ,  F01D5/18

CPC classification number: F01D5/20 ,  F01D5/187 ,  F05D2240/305 ,  F05D2240/306 ,  F05D2240/307 ,  F05D2260/202

Abstract: A blade for a gas turbine engine, including: an airfoil having a leading edge, a pressure side, a suction side and a trailing edge that extend to a tip of the airfoil; a leading edge cavity located within the airfoil; at least one main body cavity located within the airfoil; pressure side skin core passages located within the airfoil; suction side skin core passages located within the airfoil, the at least one main body cavity being fluidly isolated from the pressure side skin core passages and the suction side skin core passages and the at least one main body cavity being located between the pressure side skin core passages and the suction side skin core passages; a trailing edge feed cavity located within the airfoil; and a tip plenum located proximate to the tip of the airfoil, the tip plenum being fluidly coupled to the at least one main body cavity, wherein the tip plenum is located above the pressure side skin core passages and the trailing edge feed cavity and extends to the trailing edge of the airfoil.

公开(公告)号：US11970954B2

公开(公告)日：2024-04-30

申请号：US17971938

申请日：2022-10-24

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Brandon W. Spangler ,  David R. Pack

IPC: F01D5/18 ,  F01D5/14

CPC classification number: F01D5/188 ,  F01D5/141 ,  F05D2220/323 ,  F05D2240/301 ,  F05D2240/35 ,  F05D2250/185

Abstract: An airfoil includes an airfoil wall that defines a leading end, a trailing end, and first and second sides that join the leading end and the trailing end. A rib connects the first and second sides of the airfoil wall. The rib defines a tube portion that circumscribes a rib passage, and first and second connector arms that solely join the tube portion to, respectively, the first and second sides of the airfoil wall.

公开(公告)号：US11492912B2

公开(公告)日：2022-11-08

申请号：US16739254

申请日：2020-01-10

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Brandon W. Spangler ,  Carey Clum ,  Matthew A. Devore

IPC: F01D5/18 ,  F01D9/06 ,  F02C7/18

Abstract: A gas turbine engine component comprises a body having a leading edge, a trailing edge, and a radial span. One internal channel in the body provides an upstream supply pressure. Another internal channel in body receives the upstream supply pressure and provides a downstream supply pressure. At least one axial rib separates an internal area adjacent to the trailing edge into a plurality of individual cavities. At least one pressure regulating feature is located at an entrance to at least one individual cavity entrance to control downstream supply pressure to the trailing edge. Exits formed in the trailing edge communicate with an exit pressure. The rib and pressure regulating features cooperate such that the downstream supply pressure mimics the exit pressure along the radial span.

公开(公告)号：US11187086B2

公开(公告)日：2021-11-30

申请号：US16371239

申请日：2019-04-01

Applicant: Raytheon Technologies Corporation

Inventor： Brandon W. Spangler ,  Dominic J. Mongillo, Jr.

IPC: F01D5/18 ,  F01D9/04 ,  F01D11/08 ,  F01D25/12

Abstract: A gas turbine engine component with a core includes a first core portion configured to provide a first cooling passage. A second core portion is spaced from the first core portion and configured to provide a second cooling passage. The second core portion includes a longitudinal leg and a resupply leg transverse to and intersecting the longitudinal leg. The resupply leg has a terminal end and is configured to provide a resupply channel. A connector interconnects the terminal end to the first core portion. The connector is configured to provide a resupply hole.