Back to results
US 6,305,157 B1Granted
Gas turbine engine
AssigneeALM Development, Inc.
InventorAnatoly Rakhmailov
Life of this patent
Estimating the term…
Abstract
A gas turbine engine has a turbine blade flow portion located between a blade inlet edge and outlet edge, and having a compressor to supply a fluid flow comprising a substantial portion of the compressor fluid output along the outside surface of the blade flow portion, thus providing a thermal insulating boundary layer for the turbine blades over which flows heated fluid from the combustor. Heated fluid formed in the combustor flows without further cooling directly to the turbine blades, thereby reducing losses associated with cooling.
Claims8
A gas turbine engine comprising:
- a compressor for producing a compressed fluid flow;
- a fuel source;
- a source of combustion air;
- a casing;
- a combustion zone in said casing, said combustion zone communicating with said fuel source and with said source of combustion air to prepare a heated fluid;
- and
- a power turbine rotor disk having blades, each of said blades comprising an external airfoil surface with a leading surface and a trailing surface, an inlet edge positioned downstream of said combustion zone, an outlet edge positioned downstream of said inlet edge, a blade flow portion located adjacent said trailing surface of said external airfoil surface and between said inlet edge and said outlet edge, and an internal passage with at least one opening to said external airfoil surface, said internal passage receiving said compressed fluid from said compressor and passing said compressed fluid through said at least one opening to said blade flow portion, said compressed fluid flow moving along said blade flow portion so as to create a thermal insulating boundary between said heated fluid and said trailing surface of said external airfoil surface.
4 more elements
Dependencies are inferred from the claim text.