Rotor disc with passages

Patent metadata

Field	Value
Publication number	US-10458242-B2
Application number	US-201615333916-A
Country	US
Kind code	B2
Filing date	Oct 25, 2016
Priority date	Oct 25, 2016
Publication date	Oct 29, 2019
Grant date	Oct 29, 2019

Abstract

A rotor disc for a gas turbine engine includes an annular disc body configured to support a circumferential array of blades and having a plurality of passages defined therethrough. The passages form coils within the disc body and/or have a packing density of at least 0.1 in cross-sectional plane containing the central axis, the packing density being defined by a ratio between an open area of the passages and a solid area of the disc in the cross-sectional plane. A method of manufacturing a rotor disc is also discussed.

First claim

The invention claimed is:

1. A rotor disc for a gas turbine engine, the rotor disc comprising an annular disc body configured to support a circumferential array of blades, the disc body having a plurality of passages defined therethrough forming coils within the disc body, the passages coiled around a central axis of the disc body.

2. The rotor disc as defined in claim 1 , wherein the passages have a packing density of at least 0.1 in a cross-sectional plane of the disc body, the cross-sectional plane containing the central axis and extending in a radial direction from the central axis, the packing density defined by a ratio between an open area of the passages and a solid area of the disc in the cross-sectional plane.

3. The rotor disc as defined in claim 1 , wherein the passages are in fluid communication with an environment around the rotor disc through openings formed in a corresponding surface of the disc body at opposed ends of the passages.

4. The rotor disc as defined in claim 1 , wherein the passages have elliptical cross-sections, major axes of the elliptical cross-sections of adjacent ones of the passages having different orientations from one another.

5. The rotor disc as defined in claim 1 , wherein the passages have elliptical cross-sections, major axes of the elliptical cross-sections of adjacent ones of the coils of a same one of the passages having different orientations from one another.

6. The rotor disc as defined in claim 1 , wherein the coils of a same one of the passages are spaced along a central axis of the disc body, and the coils of adjacent ones of the passages are spaced from each other along a radial direction of the disc body.

7. The rotor disc as defined in claim 6 , wherein the adjacent passages are offset along the central axis so that in a plane containing the central axis, cross-sections of the coils of a first one of the passages have central points aligned between the central points of the cross-sections of the coils of a second one of the passages adjacent the first passage.

8. A non-axial integrally bladed rotor including the rotor disc as defined in claim 1 and an array of uncooled blades integrally connected to the rotor disc.

9. A rotor disc for a gas turbine engine, the rotor disc comprising an annular disc body configured to support a circumferential array of blades, the disc body having a plurality of passages defined therethrough, the passages having a packing density of at least 0.1 in a cross-sectional plane of the disc body, the cross-sectional plane containing the central axis and extending in a radial direction from the central axis, the packing density defined by a ratio between an open area of the passages and a solid area of the disc in the cross-sectional plane, wherein the open areas have elliptical cross-sections, major axes of the elliptical cross-sections of adjacent ones of the open areas having different orientations from one another.

10. The rotor disc as defined in claim 9 , wherein the packing density of the passages is at least 0.3.

11. The rotor disc as defined in claim 9 , wherein the packing density of the passages is at least 0.7.

12. The rotor disc as defined in claim 9 , wherein the passages are in fluid communication with an environment around the rotor through openings formed in a corresponding surface of the disc body at opposed ends of the passages.

13. The rotor disc as defined in claim 9 , wherein the passages extend at least in part around a circumference of the disc.

14. The rotor disc as defined in claim 9 , wherein the open areas of adjacent passages form radially spaced rows of open areas offset along the central axis so that in the cross-sectional plane, the open areas of one of the rows have central points aligned between the central points of the open areas of an adjacent one of the rows.

15. A rotor disc for a gas turbine engine, the rotor disc comprising an annular disc body configured to support a circumferential array of blades, the disc body having a plurality of passages defined therethrough, the passages having a packing density of at least 0.1 in a cross-sectional plane of the disc body, the cross-sectional plane containing the central axis and extending in a radial direction from the central axis, the packing density defined by a ratio between an open area of the passages and a solid area of the disc in the cross-sectional plane, wherein the open areas of adjacent passages form radially spaced rows of open areas offset along the central axis so that in the cross-sectional plane, the open areas of one of the rows have central points aligned between the central points of the open areas of an adjacent one of the rows.

Assignees

• Pratt & Whitney Canada

Inventors

• Abrari Farid

Classifications

• B22F5/009 Primary

  of turbine components other than turbine blades (of turbine blades B22F5/04) · 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

• F01D5/34

  Rotor-blade aggregates of unitary construction {, e.g. formed of sheet laminae; (discs formed of sheet laminae F01D5/028; ceramic materials F01D5/284, composite materials F01D5/282)} · CPC title

• F05D2230/50

  Building or constructing in particular ways · CPC title

• F01D5/046

  Heating, heat insulation or cooling means · CPC title