公开(公告)号：US20200340363A1

公开(公告)日：2020-10-29

申请号：US16391811

申请日：2019-04-23

Applicant: Rolls-Royce plc

Inventor： Michael J. Whittle ,  Anthony G. Razzell ,  Roderick M. Townes ,  David J. Shepherd ,  Duncan Forbes

IPC: F01D5/28 ,  F01D11/00

Abstract: A turbine assembly adapted for use in a gas turbine engine with a turbine vane comprising ceramic matrix composite materials. The turbine vane is configured to redirect air moving through a primary gas path of the gas turbine engine. The turbine assembly includes a vane-stage support for holding the turbine vane in place relative to a turbine case.

公开(公告)号：US11268392B2

公开(公告)日：2022-03-08

申请号：US16665638

申请日：2019-10-28

Applicant: Rolls-Royce plc

Inventor： Roderick M. Townes ,  Andrew T. Holt ,  Michael J. Whittle

IPC: F01D9/04 ,  F01D5/18 ,  F01D5/28 ,  B33Y10/00

Abstract: A turbine vane assembly adapted for use with a gas turbine engine includes an airfoil and a spar. The airfoil is formed to define a cavity that extends into the airfoil. The spar is located in the cavity to define a cooling passage that extends around the spar between the spar and the airfoil. The turbine vane assembly includes cooling features to aid heat transfer of the turbine vane assembly during operation in the gas turbine engine.

公开(公告)号：US11193393B2

公开(公告)日：2021-12-07

申请号：US16391827

申请日：2019-04-23

Applicant: Rolls-Royce plc

Inventor： Michael J. Whittle ,  Anthony G. Razzell ,  Roderick M. Townes ,  David J. Shepherd ,  Duncan Forbes

IPC: F01D25/24 ,  F01D9/04

Abstract: A turbine assembly adapted for use in a gas turbine engine with a turbine vane comprising ceramic matrix composite materials. The turbine vane is configured to redirect air moving through a primary gas path of the gas turbine engine. The turbine assembly includes a vane-stage support for holding the turbine vane in place relative to a turbine case.

公开(公告)号：US20210123352A1

公开(公告)日：2021-04-29

申请号：US16665638

申请日：2019-10-28

Applicant: Rolls-Royce plc

Inventor： Roderick M. Townes ,  Andrew T. Holt ,  Michael J. Whittle

IPC: F01D9/04 ,  F01D5/18 ,  F01D5/28

Abstract: A turbine vane assembly adapted for use with a gas turbine engine includes an airfoil and a spar. The airfoil is formed to define a cavity that extends into the airfoil. The spar is located in the cavity to define a cooling passage that extends around the spar between the spar and the airfoil. The turbine vane assembly includes cooling features to aid heat transfer of the turbine vane assembly during operation in the gas turbine engine.