ROTATING VANE SEAL WITH COOLING AIR PASSAGES

• US 20130108425A1
• Filed: 10/28/2011
• Published: 05/02/2013
• Est. Priority Date: 10/28/2011
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: Joseph W. Bridges Jr
• Inventors: Norris, James W., Bridges, Joseph W. Jr.
• Granted Patent: US 8,992,168 B2
• Time in Patent Office: Days
• US Class Current: 415/191
• CPC Class Codes: F01D 11/001 for sealing space between stator blade and rotor
• CPC Class Codes: F01D 11/005 Sealing means between non relatively rotating elements
• CPC Class Codes: F02C 7/12 Cooling of plants of component parts, see the relevant subclasses, e.g. F01D; cooling of engines in general F01P
• CPC Class Codes: F02C 7/18 the medium being gaseous, e.g. air F02C7/125 takes precedence
• CPC Class Codes: F04D 29/164 of an axial flow wheel
• CPC Class Codes: F04D 29/545 Ducts
• CPC Class Codes: F04D 29/547 having a special shape in order to influence fluid flow
• CPC Class Codes: F05D 2260/941 particularly aimed at mechanical or thermal stress reduction
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

An inner diameter vane seal for a gas turbine engine comprises an annular, ring-like body having inner and outer diameter rims, forward and aft faces and an air passage. The outer diameter rim extends circumferentially for engaging inner diameter ends of stator vanes. The inner diameter rim extends circumferentially and is spaced radially from the inner outer diameter rim. The forward and aft faces extend radially between the outer diameter rim and the inner diameter rim. The air passage extends from the forward face to the aft face between the inner and outer diameter rims.

Claims

1. An inner diameter vane seal for a gas turbine engine, the inner diameter vane seal comprising:

an annular, ring-like body comprising;

an outer diameter rim extending circumferentially for engaging inner diameter ends of vanes;

an inner diameter rim extending circumferentially and spaced radially from the outer diameter rim;

forward and aft faces extending radially between the outer diameter rim and the inner diameter rim; and

an air passage extending from the forward face to the aft face between the inner and outer diameter rims.

2. The inner diameter vane seal of claim 1 and further comprising:

sidewalls connecting the inner diameter rim to the outer diameter rim to define a plurality of individual air passages.

3. The inner diameter vane seal of claim 2 wherein the outer diameter rim includes a plurality of slots extending from the forward face to the aft face.

4. The inner diameter vane seal of claim 3 wherein each slot is positioned over an individual air passage.

5. The inner diameter vane seal of claim 3 wherein the slots and the individual air passages are angled with respect to a central axis of the annular, ring-like body.

6. The inner diameter vane seal of claim 3 wherein each slot includes a seal.

7. The inner diameter vane seal of claim 6 wherein the seal comprises a wire seal.

8. The inner diameter vane seal of claim 1 wherein the outer diameter rim and the inner diameter rim are comprised of different materials.

9. The inner diameter vane seal of claim 8 wherein the plurality of sidewalls include a split line where the different materials of the outer diameter rim and the inner diameter rim are joined.

10. The inner diameter vane seal of claim 1 wherein the outer diameter rim includes:

a forward seal slot extending around a circumference of the annular ring-like body; and

an aft seal slot extending around a circumference of the annular ring-like body.

11. The inner diameter vane seal of claim 1 wherein the inner diameter rim includes forward and aft hooks for engaging the forward and aft rotors.

12. The inner diameter vane seal of claim 1 wherein the outer diameter rim includes an abradable material located at an outer diameter surface.

13. A blade and vane assembly for a gas turbine engine, the assembly comprising:

an annular casing;

a forward bladed rotor assembly configured to rotate within the annular casing;

an aft bladed rotor assembly configured to rotate within the annular casing;

a plurality stator vanes cantilevered from the annular casing so as to remain stationarily disposed between the forward and aft bladed rotor assemblies; and

a sealing ring coupled to the forward and aft bladed rotor assemblies so as to be rotatable with the bladed rotor assemblies, the sealing ring comprising;

an outer diameter rim for engaging inner diameter ends of the plurality of stator vanes;

an inner diameter rim spaced radially from the outer diameter rim;

a forward face for engaging with the forward rotor assembly;

an aft face for engaging with the aft rotor assembly;

an air passage extending from the forward face to the aft face between the inner and outer diameter rims; and

sidewalls connecting the inner diameter rim to the outer diameter rim to define a plurality of individual air passages.

14. The blade and vane assembly of claim 13 wherein the outer diameter rim includes a plurality of slots extending from the forward face to the aft face.

15. The blade and vane assembly of claim 14 wherein the slots and the individual air passages are angled with respect to the sidewalls.

16. The blade and vane assembly of claim 15 wherein each slot includes a wire seal.

17. The blade and vane assembly of claim 13 wherein the outer diameter rim and the inner diameter rim are comprised of different materials.

18. The blade and vane assembly of claim 17 wherein the plurality of sidewalls include a split line where the different materials of the outer diameter rim and the inner diameter rim are joined.

19. The blade and vane assembly of claim 13 wherein the outer diameter rim includes an abradable material.

20. The blade and vane assembly of claim 13 wherein the outer diameter rim includes:

a forward seal slot extending around a circumference of the annular ring-like body; and

an aft seal slot extending around a circumference of the annular ring-like body

21. The blade and vane assembly of claim 13 wherein the inner diameter rim includes forward and aft hooks for engaging the forward and aft rotors.

22. The blade and vane assembly of claim 13 wherein the forward and aft rotors comprise turbine assemblies comprising:

a rotor disk having an outer diameter rim;

a plurality of blades extending radially from the outer diameter rim; and

a plurality of passages extending internally through the outer diameter rim.

23. The blade and vane assembly of claim 22 wherein the forward and aft rotors comprise integrally bladed rotors.

24. The blade and vane assembly of claim 22 wherein the plurality of passages aligns with the plurality of individual air passages in the sealing ring.