Turbine disk

Patent metadata

Field	Value
Publication number	US-10544677-B2
Application number	US-201715694420-A
Country	US
Kind code	B2
Filing date	Sep 1, 2017
Priority date	Sep 1, 2017
Publication date	Jan 28, 2020
Grant date	Jan 28, 2020

Abstract

A turbine rotor for a gas turbine engine includes a disk rotationally disposed about a central axis. The disk includes an annular bore portion, an annular rim portion and an annular web portion disposed radially between the bore portion and the rim portion. The annular web portion includes an aft surface. A cylindrical arm is disposed on the aft surface and has a first portion extending axially from the aft surface and a second portion extending radially outward from a distal end of the first portion. The intersection of the first portion and the aft surface defines a fillet, radially inward of the first portion. The fillet is defined by a compound radius.

First claim

What is claimed:

1. A turbine rotor, defining a central axis extending in an axial direction and a radial axis extending in a radial direction perpendicular to the central axis, comprising:
an annular bore portion;
an annular rim portion, the annular rim portion including
a blade post disposed proximate a first rim portion of the annular rim portion,
a tab disposed proximate a second rim portion disposed radially inward of the first rim portion, the tab positioned radially inward of the blade post and having an axial profile, and
a slot disposed circumferentially adjacent the tab, the slot having a roof portion that defines a roof angle extending radially outward with respect to the central axis, the roof angle ranging from 35 degrees to 45 degrees,
wherein the axial profile of the tab provides a forward facing surface that includes a blade post 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 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 post transition portion, the slope portion extending radially inward at an angle of 60 degrees to 65 degrees with respect to the central axis, and a face portion radially inward of the slope portion, the blade post transition portion defining a radius of curvature that transitions a first portion of the blade post to the slope portion;

an annular web portion disposed radially between the annular bore portion and the annular rim portion, the annular web portion having an aft surface; and
a cylindrical arm disposed on the aft surface, the cylindrical arm having a first portion extending axially from the aft surface and a second portion extending radially outward from a distal end of the first portion, an intersection of the first portion and the aft surface defining a fillet, radially inward of the first portion,
wherein the fillet is defined by a compound radius.

2. The turbine rotor of claim 1 , wherein the compound radius includes a major radius and a minor radius.

3. The turbine rotor of claim 2 , wherein the fillet further includes a first smoothing region.

4. The turbine rotor of claim 3 , wherein the first smoothing region includes a tangential intersection of the major radius and the minor radius.

5. The turbine rotor of claim 4 , wherein the fillet further includes a second smoothing region.

6. The turbine rotor of claim 5 , wherein the second smoothing region includes a tangential intersection between the minor radius and an inner radial surface of the cylindrical arm.

7. The turbine rotor of claim 6 , wherein the fillet further includes a third smoothing region that includes a tangential intersection between the major radius and the aft surface of the annular web portion, the major radius being defined by a major radius of curvature and the minor radius being defined by a minor radius of curvature.

8. The turbine rotor of claim 7 , wherein the major radius of curvature has a value greater than the minor radius of curvature.

9. The turbine rotor of claim 2 , wherein the minor radius has a radius of curvature ranging from 0.200 inches to 0.210 inches.

10. The turbine rotor of claim 9 , wherein the major radius has a radius of curvature ranging from 4.400 inches to 4.600 inches.

11. The turbine rotor of claim 10 , wherein the major radius has a radius of curvature ranging from 4.469 inches to 4.531 inches.

12. A turbine rotor, defining a central axis extending in an axial direction and a radial axis extending in a radial direction perpendicular to the central axis, comprising:
an annular bore portion;
an annular rim portion, the annular rim portion including
a blade post disposed proximate a first rim portion of the annular rim portion,
a tab disposed proximate a second rim portion disposed radially inward of the first rim portion, the tab positioned radially inward of the blade post and having an axial profile, and
a slot disposed circumferentially adjacent the tab, the slot having a roof portion that defines a roof angle extending radially outward with respect to the central axis, the roof angle ranging from 35 degrees to 45 degrees,
wherein the axial profile of the tab provides a forward facing surface that includes a blade post 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 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 post transition portion, the slope portion extending radially inward at an angle of 60 degrees to 65 degrees with respect to the central axis, and a face portion radially inward of the slope portion, the blade post transition portion defining a radius of curvature that transitions a first portion of the blade post to the slope portion;

an annular web portion disposed radially between the annular bore portion and the annular rim portion, the annular web portion having an aft surface; and
a cylindrical arm disposed on the aft surface, the cylindrical arm having a first portion extending axially outward from the aft surface,
wherein an intersection of the first portion and the aft surface defines a compound fillet positioned radially inward of the first portion, and
wherein the compound fillet is defined by a compound radius having a major radius of curvature and a minor radius of curvature.

13. The turbine rotor of claim 12 , wherein the fillet further includes a first smoothing region.

14. The turbine rotor of claim 13 , wherein the first smoothing region includes a tangential intersection of the major radius and the minor radius.

15. The turbine rotor of claim 14 , wherein the minor radius has a radius of curvature ranging from 0.200 inches to 0.210 inches.

16. The turbine rotor of claim 15 , wherein the major radius has a radius of curvature ranging from 4.469 inches to 4.531 inches.

17. The turbine rotor of claim 16 , further comprising a major radius origin and a minor radius origin,
wherein the major radius origin has a radial value within a radial range from 0.426 inches to 0.446 inches radially inward of a radially inward surface of the first portion of the cylindrical arm and an axial value within an axial range from 4.469 inches to 4.531 inches aft of the aft surface and
wherein the minor radius origin has a radial value within a radial range from 0.213 inches to 0.223 inches radially inward of the radially inward surface of the first portion of the cylindrical arm and an axial value within an axial range from 0.213 inches to 0.223 inches aft of the aft surface.

18. A turbine rotor, defining a central axis extending in an axial direction and a radial axis extending in a radial direction perpendicular to the central axis, comprising:
an annular bore portion;
an annular rim portion, the annular rim portion including
a blade post disposed proximate a first rim portion of the annular rim portion,
a tab disposed proximate a second rim portion disposed radially inward of the first rim portion, the tab positioned radially inward of the blade post and having an axial profile, and
a slot disposed circumferentially adjacent the tab, the slot having a roof portion that defines a roof angle extending radially outward with respect to the central axis, the roof angle ranging from 35 degrees to 45 degrees,
wherein the axial profile of the tab prov

Assignees

• United Technologies Corp

Inventors

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

Classifications

• F01D5/3015

  with side plates · 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

• F05D2260/941

  particularly aimed at mechanical or thermal stress reduction · CPC title

• F05D2220/32

  in gas turbines · CPC title

• H04L12/282 Primary

  based on user interaction within the home (receiver circuitry for displaying additional information being controlled by a remote control apparatus H04N21/42204) · CPC title