公开(公告)号：US10060277B2

公开(公告)日：2018-08-28

申请号：US14974545

申请日：2015-12-18

Applicant: Rolls-Royce North American Technologies, Inc. ,  Rolls-Royce Corporation

Inventor： Todd Z. Engel ,  Ted J. Freeman ,  Robert J. Shinavski ,  Ian Thomson

IPC: F01D5/32 ,  F01D5/30 ,  F01D5/28 ,  F01D5/02

CPC classification number: F01D5/3084 ,  F01D5/025 ,  F01D5/284 ,  F01D5/3007 ,  F01D5/3053 ,  F01D5/326 ,  F05D2220/32 ,  F05D2230/10 ,  F05D2230/236 ,  F05D2230/237 ,  F05D2230/60 ,  F05D2250/21 ,  F05D2260/30 ,  Y02T50/672 ,  Y02T50/673

Abstract: A turbine wheel for use in a gas turbine engine having a plurality of blades attached to a rotor disk. Each blade is formed from a composite comprising ceramic matrix material. The blades each include a root that fits within dovetail slots of the rotor disk and cooperates with a blade retention assembly to couple the blades to the rotor disk.

公开(公告)号：US20180238188A1

公开(公告)日：2018-08-23

申请号：US15438853

申请日：2017-02-22

Applicant: Rolls-Royce Corporation ,  Rolls-Royce North American Technologies, Inc.

Inventor： Brian J. Shoemaker ,  Ted J. Freeman

IPC: F01D11/08 ,  F01D25/00

CPC classification number: F01D11/08 ,  F01D25/005 ,  F01D25/246 ,  F05D2220/323 ,  F05D2230/60 ,  F05D2230/644 ,  F05D2230/72 ,  F05D2240/11 ,  F05D2260/30 ,  F05D2260/38 ,  F05D2260/83 ,  F05D2300/6033 ,  Y02T50/672

Abstract: A gas turbine engine assembly includes a turbine shroud having a carrier segment and adjacent blade track segments. The carrier segment is arranged around a central axis of the turbine shroud and the blade track segments are supported by the carrier segment.

公开(公告)号：US10047624B2

公开(公告)日：2018-08-14

申请号：US15004442

申请日：2016-01-22

Applicant: Rolls-Royce North American Technologies, Inc. ,  Rolls-Royce Corporation

Inventor： Mark O'Leary ,  Daniel K. Vetters ,  Matthew R. Brandt ,  Ted J. Freeman

IPC: F01D11/08 ,  F01D11/00 ,  F01D25/24 ,  F01D9/02 ,  F01D25/00 ,  F01D25/12

Abstract: A turbine shroud adapted for use in a gas turbine engine includes a plurality of metallic carrier segments and a plurality of blade track segments mounted to corresponding metallic carrier segments. Cooling air is directed onto the blade track segments to cool the blade track segments when exposed to high temperatures in a gas turbine engine.

公开(公告)号：US20180195940A1

公开(公告)日：2018-07-12

申请号：US15404418

申请日：2017-01-12

Applicant: Rolls-Royce Corporation ,  Rolls-Royce North American Technologies, Inc.

Inventor： Jeffrey A. Walston ,  David J. Thomas ,  Ted J. Freeman

IPC: G01N3/08 ,  G01N33/38 ,  G01N3/02

CPC classification number: G01N3/08 ,  G01M5/005 ,  G01M5/0075 ,  G01N3/02 ,  G01N3/40 ,  G01N33/388 ,  G01N2033/0003

Abstract: The present disclosure relates to a material testing system for use in testing material strength of various gas turbine engine components. The material testing system provides a load force onto portions of gas turbine engine components.

公开(公告)号：US20180156052A1

公开(公告)日：2018-06-07

申请号：US15824467

申请日：2017-11-28

Applicant: Rolls-Royce North American Technologies Inc. ,  Rolls-Royce Corporation

Inventor： Linnea Taketa ,  John Munson ,  Ted J. Freeman

IPC: F01D11/00 ,  F01D17/16 ,  F01D9/04 ,  F01D11/02 ,  F01D17/14 ,  F04D29/16 ,  F04D27/02 ,  F04D19/02 ,  F01D5/28 ,  F01D11/12 ,  F04D29/08 ,  F04D27/00 ,  F16J15/3288

CPC classification number: F01D11/005 ,  F01D5/28 ,  F01D9/041 ,  F01D11/00 ,  F01D11/02 ,  F01D11/025 ,  F01D11/122 ,  F01D17/148 ,  F01D17/162 ,  F01D17/165 ,  F04D19/02 ,  F04D27/002 ,  F04D27/0246 ,  F04D29/083 ,  F04D29/164 ,  F05B2240/571 ,  F05D2240/56 ,  F16J15/3288

Abstract: A turbomachinery component of a gas turbine engine is disclosed having a number of techniques of reducing the effects of a gap flow between an airfoil member of the gas turbine engine and a wall of the gas turbine engine. The airfoil member can be variable and in one form is a variable turbine vane. In one embodiment a brush seal is included between the vane and the wall. In another form a wear surface is disposed between the vane and the wall. In yet another form a moveable member capable of being actuated to change position can be disposed between the vane and the wall to alter the size of a gap between the two.

公开(公告)号：US20180030840A1

公开(公告)日：2018-02-01

申请号：US15711567

申请日：2017-09-21

Applicant: Rolls-Royce Corporation ,  Rolls-Royce North American Technologies Inc.

Inventor： Ted J. Freeman ,  Robert F. Proctor ,  Sean E. Landwehr ,  Adam L. Chamberlain

IPC: F01D9/02 ,  C04B37/00 ,  F01D5/18 ,  F01D5/28 ,  F01D9/04

CPC classification number: F01D9/02 ,  C04B37/005 ,  C04B2237/083 ,  C04B2237/365 ,  C04B2237/38 ,  C04B2237/61 ,  C04B2237/76 ,  C04B2237/84 ,  F01D5/189 ,  F01D5/284 ,  F01D5/288 ,  F01D9/041 ,  F01D9/044 ,  F05D2260/20 ,  F05D2300/211 ,  F05D2300/6033 ,  Y02T50/672 ,  Y02T50/673 ,  Y02T50/676 ,  Y02T50/6765

Abstract: One aspect of the present disclosure includes a turbine vane assembly comprising a vane made from ceramic matrix composite material having an outer wall extending between a leading edge and a trailing edge and between a first end and an opposing second end; an endwall made at least partially from a ceramic matrix composite material configured to engage the first end of the vane; and a retaining region including corresponding bi-cast grooves formed adjacent the first end of the vane and a receiving aperture formed in the endwall; wherein a bond is formed in the retaining region to join the vane and endwall together.

公开(公告)号：US20170370240A1

公开(公告)日：2017-12-28

申请号：US15672991

申请日：2017-08-09

Applicant: Rolls-Royce Corporation ,  Rolls-Royce North American Technologies Inc. ,  Rolls-Royce High Temperature Composites Inc. ,  Rolls-Royce plc

Inventor： Aaron D. Sippel ,  Ted J. Freeman ,  David J. Thomas ,  Joseph P. Lamusga ,  Brian J. Shoemaker ,  Steven Hillier

IPC: F01D11/00 ,  F01D5/22 ,  F01D9/04 ,  F01D25/24 ,  F01D25/26 ,  F01D5/24

CPC classification number: F01D11/005 ,  F01D5/225 ,  F01D5/24 ,  F01D9/04 ,  F01D11/008 ,  F01D25/246 ,  F01D25/26 ,  F01D25/265 ,  F05D2220/32 ,  F05D2240/11 ,  F05D2240/55 ,  F05D2300/6033 ,  Y02T50/672

Abstract: A gas turbine engine assembly adapted to separate a high pressure zone from a low pressure zone includes a seal assembly configured to block gasses from passing through the interface of two adjacent components. The seal assembly includes a rod.

公开(公告)号：US09845688B2

公开(公告)日：2017-12-19

申请号：US14138627

申请日：2013-12-23

Applicant: Rolls-Royce Corporation ,  Rolls-Royce North American Technologies, Inc.

Inventor： David J. Thomas ,  Ted J. Freeman ,  Richard C. Uskert ,  Larry A. Junod ,  Joseph Lamusga

IPC: F01D5/14 ,  F01D5/22 ,  F01D5/28

CPC classification number: F01D5/225 ,  F01D5/147 ,  F01D5/282 ,  F01D5/284 ,  F05D2300/6033 ,  Y02T50/672 ,  Y10T29/49321

Abstract: A gas turbine engine airflow member including a blade core portion, a shroud tip portion extending from the blade core portion, and an airfoil portion formed exteriorly to the blade core portion, where the blade core portion and the shroud tip portion are constructed as a first unitary structure and the airfoil portion is constructed as a second structure. A method of forming a gas turbine engine component is also disclosed.

公开(公告)号：US20160376921A1

公开(公告)日：2016-12-29

申请号：US15004436

申请日：2016-01-22

Applicant: Rolls-Royce North American Technologies, Inc. ,  Rolls-Royce Corporation

Inventor： Mark O'Leary ,  Daniel K. Vetters ,  Matthew R. Brandt ,  Ted J. Freeman

IPC: F01D25/12 ,  F01D25/00 ,  F01D9/02 ,  F01D11/08

CPC classification number: F01D25/12 ,  F01D9/02 ,  F01D11/08 ,  F01D11/20 ,  F01D25/005 ,  F01D25/246 ,  F05D2220/32 ,  F05D2240/11 ,  F05D2260/20 ,  F05D2260/201 ,  F05D2300/6033 ,  Y02T50/672 ,  Y02T50/676

Abstract: A turbine shroud adapted for use in a gas turbine engine includes a plurality of metallic carrier segments and a plurality of blade track segments mounted to corresponding metallic carrier segments. Cooling air is directed onto the blade track segments to cool the blade track segments when exposed to high temperatures in a gas turbine engine.

Abstract translation: 适用于燃气涡轮发动机的涡轮机罩包括多个金属载体段和安装到相应的金属载体段的多个叶片轨道段。 当在燃气涡轮发动机中暴露于高温时，冷却空气被引导到叶片轨道段上以冷却叶片轨道段。

公开(公告)号：US20160356164A1

公开(公告)日：2016-12-08

申请号：US15173126

申请日：2016-06-03

Applicant: Rolls-Royce North American Technologies, Inc. ,  Rolls-Royce Corporation

Inventor： Ted J. Freeman ,  Thomas D. Nixon ,  Sean E. Landwehr ,  Aaron D. Sippel ,  Donald W. Reinhart

IPC: F01D5/28 ,  F23R3/00 ,  F01D5/14 ,  B29C65/48 ,  F01D5/30 ,  F01D9/04 ,  C23C16/04 ,  B29C65/02 ,  F02C3/04 ,  F01D5/22

CPC classification number: F01D5/284 ,  B29C65/02 ,  B29C65/48 ,  B29L2031/7504 ,  F01D25/005 ,  F01D25/246 ,  F02K1/04 ,  F05D2240/11 ,  F05D2240/12 ,  F05D2300/2261 ,  F05D2300/6033 ,  F05D2300/611 ,  F05D2300/614 ,  F23M2900/05004 ,  F23R3/007 ,  F23R2900/00018

Abstract: An assembly comprising a ceramic matrix composite component, a monolithic insert, and a polymer char and a method for producing the same. The ceramic matrix composite component may include an exterior surface, with the monolithic insert bonded to the exterior surface of the ceramic matrix composite component. The polymer char may be sandwiched between the monolithic insert and the exterior surface of the ceramic matrix composite that may bond the monolithic insert to the ceramic matrix composite component.

Abstract translation: 包括陶瓷基复合材料组件，整体嵌件和聚合物炭的组件及其制造方法。 陶瓷基复合材料组件可以包括外表面，整体嵌入件结合到陶瓷基复合元件的外表面。 聚合物炭可以夹在整体式插入件和陶瓷基质复合材料的外表面之间，可将整体式嵌件与陶瓷基复合材料部件结合。