Components for gas turbine engines

• US 8,157,514 B2
• Filed: 03/19/2009
• Issued: 04/17/2012
• Est. Priority Date: 03/19/2009
• Status: Active Grant

• Current Assignee: Honeywell International Inc.
• Original Assignee: Honeywell International Inc.
• Inventors: Reyes, Victor, Urwiller, Christopher, Sandoval, Robert, Best, John
• Primary Examiner(s): Smoot, Stephen W
• Application Number:
  US12/407,534
• Publication Number:
  US 20100239422A1
• Time in Patent Office: 1,125 Days
• Field of Search: 415/199.4, 415/228, 416/204.A, 416/234, 416/237
• US Class Current: 415/199.4
• CPC Class Codes: F01D 5/10 Anti- vibration means specially adapted for radial flow machines or engines F01D5/04
• CPC Class Codes: F01D 5/26 Antivibration means not restricted to blade form or construction or to blade-to-blade connections or to the use of particular materials
• CPC Class Codes: F01D 5/34 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 Class Codes: F05D 2270/114 by limiting mechanical stresses

Abstract

A component for a gas turbine engine having an engine axis includes a rotor disk and a plurality of airfoils. The rotor disk comprises a web and a rim. The web has a first outer surface at least partially defining a plurality of holes and a plurality of slots. Each of the plurality of slots extends from a corresponding one of the plurality of holes and forms a first angle with the engine axis at the point of intersection with the corresponding one of the plurality of holes. The rim has a second outer surface also at least partially defining the plurality of slots. Each of the plurality of slots forms a second angle with the engine axis at the second outer surface, the second angle being different from the first angle. Each of the plurality of airfoils extends from the second outer surface.

Claims

1. A component for a gas turbine engine having an engine axis, the component comprising:

a rotor disk comprising;

a web having a first outer surface at least partially defining a plurality of holes and a plurality of slots, each of the plurality of slots extending from a corresponding one of the plurality of holes and forming a first angle with the engine axis at the point of intersection with the corresponding one of the plurality of holes; and

a rim having a second outer surface at least partially defining the plurality of slots, each of the plurality of slots forming a second angle with the engine axis at the second outer surface, the second angle being different from the first angle; and

a plurality of airfoils extending from the second outer surface.

2. The component of claim 1, wherein the first angle is smaller than the second angle.

3. The component of claim 1, wherein the first angle is at least approximately equal to zero.

4. The component of claim 3, wherein the second angle is approximately equal to fifteen degrees.

5. The component of claim 1, wherein each of the plurality of holes is at least approximately parallel to the engine axis.

6. The component of claim 1, wherein each of the plurality of airfoils extends from a portion of the second outer surface between two corresponding slots surrounding the portion of the second outer surface.

7. The component of claim 1, wherein the component is configured to be implemented in a turbine section of the gas turbine engine.

8. The component of claim 1, wherein the component is configured to be implemented in a compressor turbine section of the gas turbine engine.

9. The component of claim 1, wherein the component is configured to be implemented in a fan section of the gas turbine engine.

10. A turbine section for a gas turbine engine having an engine axis, the turbine section comprising:

a rotor disk comprising;

a web having a first outer surface at least partially defining a plurality of holes and a plurality of slots, each of the plurality of slots extending from a corresponding one of the plurality of holes and forming a first angle with the engine axis at the point of intersection with the corresponding one of the plurality of holes; and

a rim having a second outer surface at least partially defining the plurality of slots, each of the plurality of slots forming a second angle with the engine axis at the second outer surface, the second angle being different from the first angle; and

a plurality of turbine blades extending from the second outer surface.

11. The turbine section of claim 10, wherein the first angle is smaller than the second angle.

12. The turbine section of claim 10, wherein the first angle is at least approximately equal to zero.

13. The turbine section of claim 12, wherein the second angle is approximately equal to fifteen degrees.

14. The turbine section of claim 10, wherein each of the plurality of holes is at least approximately parallel to the engine axis.

15. The turbine section of claim 10, wherein each of the plurality of turbine blades extends from a portion of the second outer surface between two corresponding slots surrounding the portion of the second outer surface.

16. A gas turbine engine having an engine axis, the gas turbine engine comprising:

a compressor having an inlet and an outlet and operable to receive accelerated air through the inlet, compress the accelerated air, and supply the compressed air through the outlet;

a combustor coupled to receive at least a portion of the compressed air from the compressor outlet and operable to supply combusted air;

a turbine coupled to receive the combusted air from the combustor and at least a portion of the compressed air from the compressor and to generate energy therefrom, the turbine comprising;

a rotor disk comprising;

a web having a first outer surface at least partially defining a plurality of holes and a plurality of slots, each of the plurality of slots extending from a corresponding one of the plurality of holes and forming a first angle with the engine axis at the point of intersection with the corresponding one of the plurality of holes; and

a rim having a second outer surface at least partially defining the plurality of slots, each of the plurality of slots forming a second angle with the engine axis at the second outer surface, the second angle being different from the first angle; and

a plurality of turbine blades extending from the second outer surface.

17. The gas turbine engine of claim 16, wherein the first angle is smaller than the second angle.

18. The gas turbine engine of claim 16, wherein the first angle is at least approximately equal to zero.

19. The gas turbine engine of claim 18, wherein the second angle is approximately equal to fifteen degrees.

20. The gas turbine engine of claim 16, wherein each of the plurality of holes is at least approximately parallel to the engine axis.