IMPINGEMENT COOLING BAFFLE

• US 20170175578A1
• Filed: 12/21/2015
• Published: 06/22/2017
• Est. Priority Date: 12/21/2015
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Rtx Corporation)
• Inventors: Propheter-Hinckley, Tracy A.
• Granted Patent: US 10,781,715 B2
• Time in Patent Office: Days
• CPC Class Codes: F01D 25/12 Cooling
• CPC Class Codes: F01D 5/189 the insert having a tubular cross-section, e.g. airfoil shape
• CPC Class Codes: F01D 9/02 Nozzles; Nozzle boxes; Stator blades; Guide conduits , e.g. individual nozzles nozzle boxes F01D9/047
• CPC Class Codes: F01D 9/065 Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids see also F01D25/16, F01D25/24 and F01D25/26
• CPC Class Codes: F02C 3/04 having a turbine driving a compressor power transmission arrangements F02C7/36; control of working fluid flow F02C9/16
• CPC Class Codes: F05D 2220/32 in gas turbines
• CPC Class Codes: F05D 2240/80 Platforms for stationary or moving blades
• CPC Class Codes: F05D 2260/201 by impingement of a fluid
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A component for a gas turbine engine includes a first component end, a second component end and a cavity extending from the first component end to the second component end. A baffle assembly is located in the cavity including a first baffle portion inserted into the cavity and a second baffle portion inserted into the cavity. The first baffle portion overlaps the second baffle portion. A vane for a gas turbine engine includes an outer platform, an inner platform and an airfoil portion extending. A core extends through the airfoil portion. A baffle is positioned in the core and is offset from the core wall. The baffle includes a first baffle portion inserted into the core and a second baffle portion inserted into the core. One of the first baffle portion or the second baffle portion overlaps the other of the first baffle portion or the second baffle portion.

Claims

1. A component for a gas turbine engine, comprising:

a first component end;

a second component end;

a cavity extending from the first component end to the second component end; and

a baffle assembly located in the cavity including;

a first baffle portion inserted into the cavity; and

a second baffle portion inserted into the cavity;

the first baffle portion overlapping the second baffle portion.

2. The component of claim 1, wherein each of the first baffle portion and the second baffle portion include a plurality of baffle openings therethrough to direct a cooling airflow through the plurality of baffle openings to impinge on a cavity wall.

3. The component of claim 1, wherein the first baffle portion is secured to the second baffle portion.

4. The component of claim 1, further comprising a press fit condition between the first baffle portion and the second baffle portion.

5. The component of claim 1, further comprising one or more guide tabs disposed at the second baffle portion to guide the first baffle portion over the second baffle portion.

6. The component of claim 1, further comprising a cover disposed at one of the first baffle portion or the second baffle portion to at least partially block the cooling airflow from passing therethrough.

7. The component of claim 1, wherein the first baffle portion includes a retention flange to retain the first baffle portion at the first component end.

8. The component of claim 1, wherein the overlap between the first baffle portion and the second baffle portion extends from the first component end toward the second component end.

9. A vane for a gas turbine engine comprising:

an outer platform;

an inner platform;

an airfoil portion extending between the outer platform and the inner platform;

a core defined by a core wall extending through the airfoil portion from the outer platform to the inner platform;

a baffle disposed in the core and offset from the core wall, the baffle including;

a first baffle portion inserted into the core; and

a second baffle portion inserted into the core;

one of the first baffle portion or the second baffle portion overlaps the other of the first baffle portion or the second baffle portion.

10. The vane of claim 9, wherein each of the first baffle portion and the second baffle portion includes a plurality of baffle openings therethrough to direct a cooling airflow through the plurality of baffle openings to impinge on a core wall.

11. The vane of claim 9, wherein the first baffle portion is secured to the second baffle portion.

12. The vane of claim 9, further comprising a press fit condition between the first baffle portion and the second baffle portion.

13. The vane of claim 9, further comprising one or more guide tabs disposed at one of the first baffle portion or the second baffle portion to guide the other of the first baffle portion or the second baffle portion thereover.

14. The vane of claim 9, further comprising a cover disposed at one of the first baffle portion or the second baffle portion to at least partially block the cooling airflow from passing therethrough.

15. The vane of claim 9, wherein a baffle offset between the baffle and the core wall is substantially constant along the airfoil portion.

16. The vane of claim 15 wherein the baffle offset is in the range of 0.010 inches and 0.250 inches.

17. The vane of claim 9, wherein the overlap between the first baffle portion and the second baffle portion extends from the outer platform toward the inner platform.

18. A gas turbine engine, comprising:

a compressor section;

a combustor section;

a turbine section; and

a component including;

a first component end;

a second component end;

a cavity extending from the first component end to the second component end; and

a baffle assembly located in the cavity including;

a first baffle portion inserted into the cavity; and

a second baffle portion inserted into the cavity;

the first baffle portion overlapping the second baffle portion.

19. The gas turbine engine of claim 18, wherein each of the first baffle portion and the second baffle portion includes a plurality of baffle openings therethrough to direct a cooling airflow through the plurality of baffle openings to impinge on a cavity wall.

20. The gas turbine engine of claim 18, wherein the first baffle portion is secured to the second baffle portion.