Rotor disk for gas turbine engine

Patent metadata

Field	Value
Publication number	US-2020248554-A1
Application number	US-201916267935-A
Country	US
Kind code	A1
Filing date	Feb 5, 2019
Priority date	Feb 5, 2019
Publication date	Aug 6, 2020
Grant date	—

Abstract

A gas turbine engine rotor disk has a single-piece hub with a radially-outer surface, and with an annular cavity inside the single-piece hub. The annular cavity is defined by a radially-elongated cross-sectional profile revolved at least partly about the axis of rotation. Blades extend outwardly from the radially-outer surface.

First claim

1 . A gas turbine engine rotor disk, comprising:
a single-piece hub having an axis of rotation, a radially-outer surface, and an annular cavity inside the single-piece hub, the annular cavity being defined by a radially-elongated cross-sectional profile revolved at least partly about the axis of rotation; and blades extending outwardly from the radially-outer surface of the single-piece hub.

2 . The gas turbine engine rotor disk of claim 1 , wherein the single-piece hub has a shaft bore defining a radially-inner surface of the single-piece hub, and webs having radially-elongated cross-sectional profiles and spaced apart axially by the annular cavity.

3 . The gas turbine engine rotor disk of claim 1 , wherein the single-piece hub has webs having radially-elongated cross-sectional profiles and spaced apart axially by the annular cavity, the webs have a first surface and an axially-spaced apart second surface, the first and second surfaces having a concave curvature along a length thereof.

4 . The gas turbine engine rotor disk of claim 1 , wherein the single-piece hub has webs spaced apart axially by the annular cavity, the webs have a radially-elongated cross-sectional profile tapering toward a radially-outer end thereof.

5 . The gas turbine engine rotor disk of claim 1 , wherein the annular cavity has a radially-inner portion and a radially-outer portion, the radially-outer portion having a first axial dimension greater than a second axial dimension of the radially-inner portion.

6 . The gas turbine engine rotor disk of claim 1 , wherein:
the annular cavity is a first annular cavity; the single-piece hub has a second annular cavity inside the single-piece hub; the first and second annular cavities are axially-spaced apart; and a web having a radially-elongated cross-sectional profile disposed between the first and second annular cavities.

7 . The gas turbine engine rotor disk of claim 6 , wherein the first annular cavity has a first volume and the second annular cavity has a second volume different from the first volume.

8 . The gas turbine engine rotor disk of claim 1 , wherein the rotor disk is an axial compressor.

9 . The gas turbine engine rotor disk of claim 1 , wherein the rotor disk is a centrifugal impeller.

10 . A gas turbine engine, comprising:
a shaft having an axis of rotation; and a rotor disk, comprising:
a single-piece hub with a shaft bore to receive the shaft, a radially-outer surface, and an annular cavity inside the single-piece hub, the annular cavity being defined by a radially-elongated cross-sectional profile revolved at least partly about the axis of rotation, the annular cavity being disposed between axially spaced apart webs of the single-piece hub; and
blades extending outwardly from the radially-outer surface of the single-piece hub.

11 . The gas turbine engine of claim 10 , wherein the single-piece hub has a shaft bore defining a radially-inner surface of the single-piece hub, and webs having radially-elongated cross-sectional profiles and spaced apart axially by the annular cavity.

12 . The gas turbine engine of claim 10 , wherein the single-piece hub has webs having radially-elongated cross-sectional profiles and spaced apart axially by the annular cavity, the webs have a first surface and an axially-spaced apart second surface, the first and second surfaces having a concave curvature along a length thereof.

13 . The gas turbine engine of claim 10 , wherein the single-piece hub has webs spaced apart axially by the annular cavity, the webs have a radially-elongated cross-sectional profile tapering toward a radially-outer end thereof.

14 . The gas turbine engine of claim 10 , wherein the annular cavity has a radially-inner portion and a radially-outer portion, the radially-outer portion having a first axial dimension greater than a second axial dimension of the radially-inner portion.

15 . The gas turbine engine of claim 10 , wherein:
the annular cavity is a first annular cavity; the single-piece hub has a second annular cavity inside the single-piece hub; the first and second annular cavities are axially-spaced apart; and a web having a radially-elongated cross-sectional profile disposed between the first and second annular cavities.

16 . The gas turbine engine of claim 15 , wherein the first annular cavity has a first volume and the second annular cavity has a second volume different from the first volume.

17 . The gas turbine engine of claim 10 , wherein the rotor disk is an axial compressor.

18 . The gas turbine engine of claim 10 , wherein the rotor disk is a centrifugal impeller.

Assignees

• Pratt & Whitney Canada

Inventors

• Ho Eric
• Zeinalov Jamal

Classifications

• F01D5/048 Primary

  Form or construction · CPC title

• F01D5/02 Primary

  Blade-carrying members, e.g. rotors (rotors of non-bladed type F01D1/34; stators F01D9/00 {; selecting particular materials F01D5/28}) · CPC title

• B22F10/20

  Direct sintering or melting · CPC title

• B22F2998/10

  Processes characterised by the sequence of their steps · CPC title

• Y02P10/25

  Process efficiency · CPC title