公开(公告)号：US10760423B2

公开(公告)日：2020-09-01

申请号：US15947119

申请日：2018-04-06

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Stephen P. Muron ,  Ioannis Alvanos ,  Christopher M. Dye ,  Brian D. Merry ,  Arthur M. Salve, Jr. ,  James W. Norris

IPC: F01D5/02 ,  F01D5/06

Abstract: A rotor for a gas turbine engine includes a plurality of blades which extend from a rotor disk at an interface, where the interface is defined along a spoke. A spool for a gas turbine engine includes the rotor disk, the plurality of blades with the interface defined along the spoke radially inboard of a blade platform, a rotor ring axially adjacent to the rotor disk, and a plurality of core gas path seals which extend from the rotor ring. Each of the plurality of core gas path seals extends from the rotor ring at a seal interface, with the seal interface defined along a spoke and the plurality of core gas path seals being axially adjacent to the blade platform.

公开(公告)号：US20180223668A1

公开(公告)日：2018-08-09

申请号：US15947119

申请日：2018-04-06

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Stephen P. Muron ,  Ioannis Alvanos ,  Christopher M. Dye ,  Brian D. Merry ,  Arthur M. Salve, JR. ,  James W. Norris

IPC: F01D5/02 ,  F01D5/06

Abstract: A rotor for a gas turbine engine includes a plurality of blades which extend from a rotor disk at an interface, where the interface is defined along a spoke. A spool for a gas turbine engine includes the rotor disk, the plurality of blades with the interface defined along the spoke radially inboard of a blade platform, a rotor ring axially adjacent to the rotor disk, and a plurality of core gas path seals which extend from the rotor ring. Each of the plurality of core gas path seals extends from the rotor ring at a seal interface, with the seal interface defined along a spoke and the plurality of core gas path seals being axially adjacent to the blade platform.

公开(公告)号：US09790792B2

公开(公告)日：2017-10-17

申请号：US14302884

申请日：2014-06-12

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gabriel L. Suciu ,  Stephen P. Muron ,  Christopher M. Dye ,  Ioannis Alvanos ,  Brian D. Merry

IPC: F01D5/02 ,  F01D5/14 ,  F01D5/06 ,  F01D11/00

CPC classification number: F01D5/02 ,  F01D5/022 ,  F01D5/025 ,  F01D5/027 ,  F01D5/066 ,  F01D5/14 ,  F01D5/147 ,  F01D11/006 ,  F05D2240/20 ,  F05D2260/15 ,  Y10T29/49316 ,  Y10T29/4932

Abstract: A spool for a gas turbine engine includes at least one rotor disk defined along an axis of rotation and at least one rotor ring defined along the axis of rotation, with the rotor ring being in contact with the rotor disk. The rotor disk and rotor ring are contoured to define a smooth rotor stack load path.

公开(公告)号：US20140294589A1

公开(公告)日：2014-10-02

申请号：US14302884

申请日：2014-06-12

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gabriel L. Suciu ,  Stephen P. Muron ,  Christopher M. Dye ,  Ioannis Alvanos ,  Brian D. Merry

IPC: F01D5/02

CPC classification number: F01D5/02 ,  F01D5/022 ,  F01D5/025 ,  F01D5/027 ,  F01D5/066 ,  F01D5/14 ,  F01D5/147 ,  F01D11/006 ,  F05D2240/20 ,  F05D2260/15 ,  Y10T29/49316 ,  Y10T29/4932

Abstract: A spool for a gas turbine engine includes at least one rotor disk defined along an axis of rotation and at least one rotor ring defined along the axis of rotation, with the rotor ring being in contact with the rotor disk. The rotor disk and rotor ring are contoured to define a smooth rotor stack load path.

Abstract translation: 用于燃气涡轮发动机的线轴包括沿着旋转轴线限定的至少一个转子盘和沿着旋转轴线限定的至少一个转子环，转子环与转子盘接触。 转子盘和转子环形成轮廓以限定平滑的转子堆叠负载路径。