Turbine disk

Patent metadata

Field	Value
Publication number	US-10550702-B2
Application number	US-201715694499-A
Country	US
Kind code	B2
Filing date	Sep 1, 2017
Priority date	Sep 1, 2017
Publication date	Feb 4, 2020
Grant date	Feb 4, 2020

Abstract

A turbine rotor disk for a gas turbine engine includes a disk rotationally disposed about a central axis. The disk includes a bore, a rim and a web disposed radially between the bore and the rim. The rim includes a first radially outermost rim portion and a second radially outermost rim portion disposed radially inward of the first radially outermost rim portion. First and second blade posts are disposed proximate the first radially outermost rim portion and spaced circumferentially. First and second tabs are disposed proximate the second radially outermost rim portion and positioned radially inward of the first and second blade posts. A slot is disposed circumferentially between the first tab and the second tab. The first tab and the second tab have an axial profile that includes a blade post transition portion, a slope portion radially inward of the blade transition portion and a face portion radially inward of the slope portion.

First claim

What is claimed:

1. A turbine rotor, comprising:
a disk rotationally disposed about a central axis, the disk including
a bore,
a rim and
a web disposed radially between the bore and the rim;
a first rim portion and a second rim portion, the second rim portion disposed radially inward of the first rim portion;
the first rim portion including a first blade post and a second blade post, the second blade post spaced circumferentially a distance from the first blade post;
the second rim portion including a first tab positioned radially inward of the first blade post and a second tab positioned radially inward of the second blade post;
a slot disposed circumferentially between the first tab and the second tab;
a third blade post positioned circumferentially between the first blade post and the second blade post and radially outward of the slot,
wherein the first tab and the second tab have an axial profile, when viewed in a circumferential direction, that includes a blade post transition portion which directly connects two different axially facing surfaces, the blade transition portion disposed circumferentially adjacent a radially inward most branch of a plurality of branches spaced radially between a base and a tip of the first blade post and the second blade post and at a radial distance from the central axis equal to that of the radially inward most branch; a slope portion radially inward of the blade transition portion; and a face portion radially inward of the slope portion; and the slot has a circumferential length equal to a circumferential length of each of the first tab and the second tab measured at the face portion.

2. The turbine rotor of claim 1 , wherein the slot has a circumferential length ranging from 0 0.910 inches to 0 0.930 inches.

3. The turbine rotor of claim 1 , wherein the tip and the base of the first blade post define a length in the radial direction and wherein the blade post transition portion is disposed at a location between 25% and 50% of the length in the radially outward direction.

4. The turbine rotor of claim 3 , wherein the slope portion of the first tab extends radially inward from the blade post transition portion.

5. The turbine rotor of claim 4 , wherein the slope portion of the first tab extends radially inward from the blade post transition portion at an angle with respect to the central axis and wherein the slope portion merges with the face portion.

6. The turbine rotor of claim 4 , wherein the slope portion extends radially inward at an angle of 60 degrees to 65 degrees with respect to the central axis and wherein the blade post transition portion has a radius of curvature of 0.194 inches to 0.214 inches.

7. The turbine rotor of claim 5 , wherein the slope portion extends radially inward at an angle of 60 degrees to 65 degrees with respect to the central axis and wherein the face portion extends radially inward at an angle of 85 degrees to 95 degrees with respect to the central axis.

8. The turbine rotor of claim 7 , wherein a radial length between the blade transition portion and a radially outermost point of the face portion ranges from 0.590 inches to 0.600 inches.

9. A turbine rotor, comprising:
a disk rotationally disposed about a central axis, the disk including
a bore,
a rim and
a web disposed radially between the bore and the rim;
a plurality of blade posts disposed on and spaced circumferentially about a radially outermost portion of the disk;
a plurality of tabs disposed on and spaced circumferentially about a portion of the disk radially inward from the radially outermost portion of the disk, each tab having an axial profile, when viewed in a circumferential direction, and
a plurality of slots circumferentially interspersed between adjacent pairs of tabs,
wherein the axial profile of each one of the plurality of tabs includes a blade post transition portion which directly connects two different axially facing surfaces, the blade transition portion disposed circumferentially adjacent a radially inward most branch of a plurality of branches spaced radially between a base and a tip of each of the plurality of blade posts and at a radial distance from the central axis equal to that of the radially inward most branch; a slope portion radially inward of the blade transition portion; and a face portion radially inward of the slope portion; and each of the plurality of slots has a circumferential length equal to a circumferential length of each of the plurality of tabs measured at the face portion.

10. The turbine rotor of claim 9 , wherein the slope portions extend radially inward from the blade post transition portions at an angle with respect to the central axis and wherein the slope portions merge with the face portions.

11. The turbine rotor of claim 10 , wherein the blade post transition portions have a radius of curvature of 0 0.194 inches to 0.214 inches.

12. The turbine rotor of claim 11 , wherein the slope portions extend radially inward at an angle of between 60 degrees and 65 degrees with respect to the central axis.

13. The turbine rotor of claim 12 , wherein the slope portions extend radially inward at an angle of 62 degrees with respect to the central axis and wherein each corresponding face portion extends radially inward at an angle of 90 degrees with respect to the central axis.

14. The turbine rotor of claim 9 , wherein a slot is disposed radially inward of alternating blade posts.

15. The turbine rotor of claim 9 , wherein the number of slots equals 41 and wherein each slot has a circumferential length ranging from 0 0.910 inches to 0.930 inches.

16. A turbine rotor, comprising:
a disk rotationally disposed about a central axis, the disk including
a bore,
a rim and
a web disposed radially between the bore and the rim;
a plurality of blade posts disposed on and spaced circumferentially about a radially outermost portion of the disk;
a plurality of tabs disposed on and spaced circumferentially about a portion of the disk radially inward from the radially outermost portion of the disk, each tab having an axial profile, when viewed in a circumferential direction; and
a plurality of slots interspersed between adjacent pairs of tabs;
wherein the axial profile of each one of the plurality of tabs includes a blade post transition portion which directly connects two different axially facing surfaces, the blade transition portion disposed circumferentially adjacent a radially inward most branch of a plurality of branches spaced radially between a base and a tip of each of the plurality of blade posts and at a radial distance from the central axis equal to that of the radially inward most branch; a slope portion merging with and extending radially inward of the blade post transition portion; and a face portion merging with and extending radially inward of the slope portion; and each of the plurality of slots has a circumferential length equal to a circumferential length of each of the plurality of tabs measured at the face portion.

17. The turbine rotor of claim 16 , wherein the blade post transition portions have a radius of curvature of 0.194 inches to 0.214 inches, wherein the slope portions extend radially inward at an angle of 60 degrees to 65 degrees with respect to the central axis, wherein the face portions extend radially inward at an angle of 85 degrees to 95 degrees with respect to the central axis and wherein the number of slots equals 41 and each slot has a circumferential length ranging from 0.910 inches to 0.930 inches.

Assignees

• United Technologies Corp

Inventors

• Leon Jeffrey
• Indoe William
• Caruso Kimberly
• Burke Brian J
• Leach Kurt
• Betancourt Fabian D

Classifications

• F01D5/323

  Locking of axial insertion type blades by means of a key or the like parallel to the axis of the rotor · CPC title

• F01D5/3015 Primary

  with side plates · CPC title

• F01D11/001

  for sealing space between stator blade and rotor · CPC title

• F01D5/326

  Locking of axial insertion type blades by other means · CPC title

• F01D5/02

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