公开(公告)号：US20220098988A1

公开(公告)日：2022-03-31

申请号：US17429097

申请日：2020-02-07

Applicant: Raytheon Technologies Corporation

Inventor： Nicholas M. LoRicco ,  Parth Jariwala ,  Alex J. Schneider ,  Bret M. Teller ,  Matthew S. Gleiner ,  Jeffrey T. Morton

IPC: F01D5/18 ,  F01D5/08

Abstract: A turbine blade has an attachment root and an airfoil. A cooling passageway system has a plurality of trunks extending from respective inlets along the root inner diameter end from a leading trunk near a first axial end to a trailing trunk near a second axial end; and a plurality of outlets along the airfoil including trailing edge outlets fed by the trailing trunk. Viewed normal to a root end-to-end centerplane: the trailing trunk has a turn passing forward and then rearward; an outside of the turn protrudes forward; and the outside of the turn has a tighter curvature than an inside of the turn.

公开(公告)号：US10947853B2

公开(公告)日：2021-03-16

申请号：US16581895

申请日：2019-09-25

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Matthew A. Devore ,  Matthew S. Gleiner

IPC: F01D5/18 ,  F01D25/12 ,  F01D9/02

Abstract: A gas turbine engine component includes an airfoil that has a leading edge and extends from a first side of a platform that has a leading edge overhang. A root portion extends from a second side of the platform opposite the first side. A cooling passage extends through the platform and beneath a trailing edge of the airfoil. The cooling passage includes an inlet located on a second opposite side of the platform. The inlet is located axially upstream of the leading edge of the airfoil and the inlet is located axially upstream of the root portion in the leading edge overhang.

公开(公告)号：US11661852B2

公开(公告)日：2023-05-30

申请号：US17429097

申请日：2020-02-07

Applicant: Raytheon Technologies Corporation

Inventor： Nicholas M. LoRicco ,  Parth Jariwala ,  Alex J. Schneider ,  Bret M. Teller ,  Matthew S. Gleiner ,  Jeffrey T. Morton

IPC: F01D5/18 ,  F01D5/08

CPC classification number: F01D5/187 ,  F01D5/087 ,  F05D2240/304 ,  F05D2250/711 ,  F05D2250/712 ,  F05D2260/201

Abstract: A turbine blade has an attachment root and an airfoil. A cooling passageway system has a plurality of trunks extending from respective inlets along the root inner diameter end from a leading trunk near a first axial end to a trailing trunk near a second axial end; and a plurality of outlets along the airfoil including trailing edge outlets fed by the trailing trunk. Viewed normal to a root end-to-end centerplane: the trailing trunk has a turn passing forward and then rearward; an outside of the turn protrudes forward; and the outside of the turn has a tighter curvature than an inside of the turn.