Platform with cooling circuit

• US 8,714,909 B2
• Filed: 12/22/2010
• Issued: 05/06/2014
• Est. Priority Date: 12/22/2010
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Propheter-Hinckley, Tracy A.
• Primary Examiner(s): Look, Edward
• Assistant Examiner(s): Flores, Juan G
• Application Number:
  US12/975,416
• Publication Number:
  US 20120163975A1
• Time in Patent Office: 1,231 Days
• Field of Search: 415/115, 415/191, 415/211.2, 298/892, 298/897, 298/897.1, 298/897.2, 298/897.21, 298/897.22, 295/271, 295/275
• US Class Current: 415/115
• CPC Class Codes: F01D 11/24 by selectively cooling-heating stator or rotor components
• CPC Class Codes: F01D 9/041 using blades F01D5/148 takes precedence
• CPC Class Codes: F05D 2230/21 by casting
• CPC Class Codes: F05D 2230/232 by welding
• CPC Class Codes: F05D 2240/11 Shroud seal segments
• CPC Class Codes: F05D 2240/81 Cooled platforms
• CPC Class Codes: F05D 2260/201 by impingement of a fluid
• CPC Class Codes: F05D 2260/202 by film cooling
• CPC Class Codes: F05D 2260/204 by the use of microcircuits
• CPC Class Codes: F05D 2260/205 Cooling fluid recirculation, i.e. after cooling one or more components is the cooling fluid recovered and used elsewhere for other purposes
• CPC Class Codes: F05D 2260/2212 by creating turbulence vortex generators, turbulators or the like for mixing F05D2240/127
• CPC Class Codes: F05D 2260/22141 using fins or ribs
• CPC Class Codes: Y10T 29/49341 with cooling passage

Abstract

A turbine engine component has an airfoil portion, which airfoil portion is bounded by a platform at one end. The platform has an as-cast open cavity bordered by at least one as-cast landing. A plate is welded to the at least one as-cast landing to cover and close the as-cast open cavity. A process for forming the turbine engine component is described.

Claims

1. A turbine engine component comprising:

an airfoil portion;

said airfoil portion being bounded by a platform at one end;

said platform having an as-cast open cavity bordered by at least one as-cast landing;

a plate welded to said at least one as-cast landing to cover said as-cast open cavity; and

said cavity having an entrance area and said plate having an opening which overlies said entrance area wherein said opening is in a trailing edge portion of said plate.

2. The turbine engine component of claim 1, further comprising said cavity having an exit area in a trailing edge portion thereof and said exit area having a plurality of holes for directing cooling air over a hot gas path side of said platform.

3. The turbine engine component of claim 1, further comprising said cavity having a plurality of as-cast, integrally formed protuberances.

4. The turbine engine component of claim 1, further comprising said cavity having at least one as-cast, integrally formed trip strip.

5. The turbine engine component of claim 1, wherein said as-cast landing circumscribes said cavity.

6. The turbine engine component of claim 1, wherein said platform is an outer platform and wherein said component has an inner platform and said airfoil portion extends between said inner and outer platforms.

7. The turbine engine component according to claim 1, wherein said airfoil portion has a pressure side, a suction side, and at least one internal cavity and said platform cavity is located in proximity to said at least one internal cavity and adjacent one of said pressure side and said suction side.

8. The turbine engine component of claim 1, further comprising said cavity having an exit area in a leading edge portion thereof and said exit area having a plurality of holes for directing cooling air over a hot gas path side of said platform.

9. A process for forming a turbine engine component comprising the steps of:

casting a turbine engine component having an airfoil portion with a pressure side and a suction side and a platform with an open cavity and a landing positioned on a periphery of said cavity;

positioning a plate over an opening in said open cavity, wherein said positioning step comprises positioning said plate with an opening over an entrance area in said open cavity wherein said opening is in a trailing edge portion of said plate; and

welding said plate to said landing to close said cavity.

10. The process of claim 9, wherein said casting step comprises casting a plurality of protuberances positioned within said cavity.

11. The process of claim 9, wherein said casting step comprises forming at least one trip strip in said cavity.

12. The process of claim 9, further comprising forming a plurality of cooling fluid exit holes in said cavity.

13. The process of claim 9, wherein said landing circumscribes a periphery of said cavity.

14. The process of claim 9, wherein said airfoil portion has a chord line and said casting step comprises forming said open cavity on one of a pressure side and a suction side of said chord line.

15. The process of claim 9, further comprising forming at least one internal cavity in said airfoil portion using at least one core.

16. A turbine engine component comprising:

an airfoil portion;

said airfoil portion being bounded by a platform at one end;

said platform having an as-cast open cavity bordered by at least one as-cast landing; and

a plate welded to said at least one as-cast landing to cover said as-cast open cavity, wherein said cavity having an entrance area and said plate having an opening which overlies said entrance area, said opening is in a trailing edge portion of said plate said cavity having an exit area in a leading edge portion thereof and said exit area having a plurality of holes for directing cooling air over a hot gas path side of said platform.