GAS TURBINE ENGINE BLADES

• US 3,782,852 A
• Filed: 08/22/1972
• Issued: 01/01/1974
• Est. Priority Date: 08/25/1971
• Status: Expired due to Term

• Current Assignee: Alan Moore
• Original Assignee: Alan Moore
• Inventors: Moore, Alan
• Primary Examiner(s): Powell, Jr., Everette A.
• Application Number:
  US05/282,779
• Time in Patent Office: 497 Days
• Field of Search: 416/96-97 415/115
• US Class Current: 416/97.00R
• CPC Class Codes: F01D 5/188 with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall

Abstract

A gas turbine blade has a hollow interior space in which is disposed a double-walled insert. The insert forms chambers with the blade walls, and together with the interior of the insert these chambers form part of a path for the flow of cooling fluid through the blade. The chambers provide separated in-flow and out-flow chamber(s), arranged so that cooling fluid supplied from one end of the blade passes through the in-flow chambers to the interior of the insert at the leading edge of the blade, and from there passes to the trailing edge of the blade where it leaves the blade by way of the out-flow chamber(s).

Claims

1. A gas turbine blade having opposed walls defining therebetween a hollow interior space, a double-walled insert within said space, and means defining two inflow chambers between said insert and said walls, one on each side of the insert, and at least one out-flow chamber, the insert interior communicating with the in-flow chambers in the region of the leading edge of the insert and communicating with said out-flow chamber in the region of the trailing edge thereof, the in-flow chambers being arranged for supply with cooling fluid at one end of the blade.

2. A blade as claimed in claim 1, where the in-flow and out-flow chambers are separated from one another by fins integrally formed on the interior surfaces of the blade walls and abutting the insert on either side thereof.

3. A blade as claimed in claim 1 wherein location for the insert within the blade is provided by a plurality of projections integrally forMed on the interior surfaces of each blade wall and abutting the insert on either side thereof.

4. A blade as claimed in claim 3, wherein at least some of the projections are in the form of fins arranged to guide cooling fluid from the said one end of the blade towards the other end thereof.

5. A blade as claimed in claim 1, wherein the interior of the insert communicates along the leading edge of the insert with a chamber common to the in-flow chambers and separating the leading edges of the blade and the insert, the walls of the insert being maintained in spaced relation by the plurality of spacers.

6. A blade as claimed in claim 1, wherein a plurality of apertures are formed in the region of the leading edge of the blade for allowing cooling fluid to pass to the exterior of the blade from the inflow chambers.

7. A blade as claimed in claim 1, wherein a plurality of apertures are formed in the region of the trailing edge of the blade for allowing cooling fluid to pass to the exterior of the blade from the out-flow chamber(s).

8. A gas turbine rotor having a plurality of blades as claimed in claim 1 arranged for supply with cooling fluid at their root ends.

9. A blade as claimed in claim 1, which includes one or more bleed holes connecting the inflow chambers and the outflow chamber(s) directly together at the said one end of the blade.

10. A blade as claimed in claim 1, wherein the insert is mounted within the blade by brazing at one end thereof, being otherwise unattached to allow for differential expansion.