Patent Number: 6,254,334

Title: Method and apparatus for cooling a wall within a gas turbine engine

Abstract: According to the present invention, a method and an apparatus for cooling a wall within a gas turbine engine is provided. The apparatus includes and the method provides for a cooling circuit disposed within a wall having utility within a gas turbine engine. The cooling circuit includes a forward end, an aft end. The pedestals extend between first and second portions of the wall. The characteristics and array of the pedestals within the cooling circuit are chosen to provide a heat transfer cooling profile within the cooling circuit that substantially offsets the profile of the thermal load applied to the wall portion containing the cooling circuit. At least one inlet aperture provides a cooling airflow path into the forward portion of the cooling circuit from the cavity. A plurality of exit apertures provide a cooling airflow path out of the aft portion of the cooling circuit and into the core gas path outside the wall.

Inventors: LaFleur; Ronald S. (Potsdam, NY)

Assignee: United Technologies Corporation

International Classification: F01D 5/18 (20060101); F01D 005/14 ()

Expiration Date: 07/03/2018