GAS TURBINE ENGINE BLADES

• US 3,806,274 A
• Filed: 08/22/1972
• Issued: 04/23/1974
• 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:
  US05/282,778
• Time in Patent Office: 609 Days
• Field of Search: 416/96-97,92
• 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 which is divided to form flow passages for cooling medium. The flow passages are bounded by the sides of a sheet-like insert the two blade walls, and fins between the insert and the blade walls; they commence at one end of the blade and extend in a spiral-like path around the opposite sides of the insert.

Claims

1. A gas turbine blade having opposed walls defining therebetween a hollow interior space, an insert within said space, said insert being formed of a solid sheet curved to the chamber of the blade, and fins carried by said blade and extending between said insert and said blade walls, said walls, said insert and said fins defining in combination a plurality of flow passages for cooling fluid, each said flow passage commencing at one end of the blade and extending in a spiral-like manner around and along the insert.

2. A blade as claimed in claim 1, which includes a plurality of discrete pimples extending between the sides of the insert and the blade walls within the flow passages for providing location for the insert.

3. A blade as claimed in claim 2, wherein the fins and pimples are formed integrally with the blade walls.

4. A blade as claimed in claim 1, wherein holes 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 flow passages.

5. A blade as claimed in claim 1, wherein holes 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 flow passages.

6. A blade as claimed in claim 1, wherein the insert has a root end portion at which it is secured within the blade by brazing, the insert being otherwise unattached to allow for differential expansion.

7. A blade as claimed in claim 1, wherein at least some of the flow passages are arranged for individually serving one edge only of the blade.

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 gas turbine rotor according to claim 8, which includes a shroud connecting together the outer ends of the blades, the arrangement being such that cooling fluid may pass from said flow passages into cooling relation with the shroud.

10. A rotor according to claim 9, wherein the radially inner surface of the shroud is formed with channels, and the blade walls are formed with holes arranged for directing cooling fluid from the flow passages along the channels.

11. A blade as claimed in claim 6, wherein said fins are terminated immediately adjacent said root end portion of said insert.

12. A gas turbine blade having opposed walls defining therebetween a hollow interior space, and an insert within said space, said insert being formed of a solid sheet curved to the chamber of the blade and connected to said walls by brazing at the root end of the blade, being otherwise unattached to allow for differential expansion, said walls being integrally formed with fins extending between said insert and said blade walls, said walls, said insert and said fins defining in combination a plurality of flow passages for cooling fluid to flow through the blade commencing at the root end of the blade and passing in a spiral-like manner around and along the insert.