Turbine vane having dedicated inner platform cooling

• US 5,344,283 A
• Filed: 01/21/1993
• Issued: 09/06/1994
• Est. Priority Date: 01/21/1993
• Status: Expired due to Term

• Current Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Pawlaczyk, Richard J., Schwarz, Richard A. Jr., Magowan, John W., Pighetti, Annette M.
• Primary Examiner(s): KWON, JOHN
• Application Number:
  US08/008,959
• Time in Patent Office: 593 Days
• Field of Search: 415/115, 415/116, 416/193 A
• US Class Current: 415/115
• CPC Class Codes: F01D 5/187 Convection cooling
• CPC Class Codes: F01D 9/041 using blades F01D5/148 takes precedence
• 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

Abstract

A turbine vane for a gas turbine engine core adaptable to be operated in a variety of thrust regimes is disclosed. Various construction details are developed which provide cooling to an inner platform of the turbine vane. In one particular embodiment, a turbine vane includes a hollow core permitting cooling fluid to pass through the vane and an inner platform having a pocket disposed therein, the pocket being in fluid communication with the core. Heat is exchanged between the platform and the cooling fluid within the pocket. Cooling holes extend between the pocket and a flow surface of a platform to provide cooling of the flow surface.

Claims

1. A turbine vane for a gas turbine engine disposed about a longitudinal axis and having an axially oriented annular flow path therethrough, the gas turbine engine including a compressor section, a combustor section, a turbine section downstream of the combustor section, and a source of cooling fluid, the turbine section including the turbine vane, wherein the turbine vane includes:

an airfoil portion extending through the flow path, the airfoil portion including a hollow core therein, the core being open at its radially outer end to define a passage for conducting cooling fluid from the source through the airfoil portion;

a platform portion disposed radially inwardly of the airfoil portion and oppositely of the open end of the core, the platform having a radially outer surface defining a flow surface for working fluid within the flow path, the platform including a plurality of pockets and a plurality of cooling holes, each of the pockets having a cooling passage permitting fluid communication with the core such that cooling fluid is exchanged between the core and the pocket to thereby transfer heat from the platform to the fluid within the pocket, and the cooling holes extending between each of the pockets and the flow surface and defining means to eject cooling fluid over the flow surface of the platform.

2. The turbine vane according to claim 1, wherein the airfoil portion includes a leading edge and one of the plurality of pockets extends into the region of the platform which is axially upstream of the leading edge of the airfoil portion.

3. The turbine vane according to claim 1, wherein the airfoil portion includes a pressure surface and one of the plurality of pockets extends into the region of the platform which is adjacent to the pressure surface of the airfoil portion.

4. The turbine vane according to claim 1, wherein the airfoil portion includes a trailing edge and one of the plurality of pockets extends into the region of the platform which is axially downstream of the trailing edge of the airfoil portion.

5. The turbine vane according to claim 2, further including a pressure surface disposed on the airfoil portion and wherein one of the plurality of pockets extends into the region of the platform which is adjacent to the pressure surface of the airfoil portion.

6. The turbine vane according to claim 2, further including a trailing edge disposed on the airfoil portion and wherein one of the plurality of pockets extends into the region of the platform which is axially downstream of the trailing edge of the airfoil portion.

7. The turbine vane according to claim 5, further including a trailing edge disposed on the airfoil portion and wherein one of the plurality of pockets extends into the region of the platform which is axially downstream of the trailing edge of the airfoil portion.