COOLED VANE OR BLADE FOR A GAS TURBINE ENGINE

• US 3,799,696 A
• Filed: 06/29/1972
• Issued: 03/26/1974
• Est. Priority Date: 07/02/1971
• Status: Expired due to Term

• Current Assignee: Robert Frederick Redman
• Original Assignee: Robert Frederick Redman
• Inventors: Redman, Robert Frederick
• Primary Examiner(s): Powell, Jr., Everette A.
• Application Number:
  US05/267,581
• Time in Patent Office: 635 Days
• Field of Search: 416/96-97,90 415/115
• US Class Current: 416/97.00R
• CPC Class Codes: F01D 5/189 the insert having a tubular cross-section, e.g. airfoil shape
• CPC Class Codes: F05D 2250/185 serpentine-like

Abstract

A hollow cooled blade or vane for a gas turbine engine comprises a hollow leading edge portion given substantially unrestricted access to a source of cooling air and provided with film cooling holes to the blade outer surface, a hollow center portion with an air entry tube supplied with cooling air and apertured to cause the air to impinge on the blade inner surface, and a trailing edge portion having a sinuous passage for cooling air therein.

Claims

1. A cooled vane or blade for a gas turbine engine comprising a hollow leading edge blade portion having substantially unrestricted access to an exterior blade part adapted to be supplied with cooling air, said unrestricted access providing direct cooling to the interior surface of said hollow leading edge portion, the leading edge portion being provided with holes from the inner to the outer surface to provide film cooling, a hollow center blade portion separate from said hollow leading edge portion and comprising an air entry tube open to said exterior part and apertured to cause the air to impinge upon the inner surface of the central portion, said center portion having film cooling holes passing from the interior to the exterior surface thereof, and a trailing edge blade portion having a sinuous passage for cooling air extending therein.

2. A cooled vane or blade as claimed in claim 1 and in which said blade comprises an aerofoil section and said exterior part supplied with cooling air comprises the surface of the shroud or platform distant from the aerofoil section.

3. A cooled blade as claimed in claim 1 and comprising further film cooling holes passing from the interior to the exterior surface of the blade in said trailing edge portion.

4. A cooled vane or blade as claimed in claim 1 and in which air flows to said sinuous passage from said central portion.

5. A cooled vane or blade as claimed in claim 1 and comprising a longitudinally extending trailing edge slot from which the air may flow having passed along the passage.

6. A cooled vane or blade as claimed in claim 1 and in which the air entry tube is formed by a pair of apertured sheets lying approximately parallel with the blade flanks and a pair of diaphragms which divide the blade into its leading edge, central and trailing edge portions.