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US 4,893,987 AGranted
Diffusion-cooled blade tip cap
AssigneeGeneral Electric Company
InventorsChing P. Lee, Eugene T. Vaughn, Nicholas C. Palmer
Life of this patent
Estimating the term…
Abstract
An improved turbine blade tip with diffusion cooling holes in the tip is disclosed. One particular embodiment of the invention provides an improved squealer blade tip with diffusion cooling holes in the tip. Yet another embodiment of the invention provides blade tip diffusion cooling holes comprising a first cylindrical portion coupled to a second conical portion.
Claims36
A gas turbine engine cooled turbine blade tip comprising:
- an endwall having at least one diffusion cooling hole for passing cooling flow therethrough.
A gas turbine engine coolable turbine blade squealer tip comprising:
- an endwall including a radially inner cool side and a radially outer hot side having at least one diffusion cooling hole therethrough and a squealer tip wall extending radially outward from said hot side.
A squealer type turbine blade comprising:
- a cooling chamber radially outwardly capped by an endwall,
- said endwall including a radially inner cool side and a radially outer hot side having at least one diffusion cooling hole therethrough, and
- a squealer tip wall extending radially outward from said hot side.
A coolable turbine blade comprising:
- a cooling chamber radially outwardly capped by an endwall, and
- said endwall includes at least one diffusion cooling hole therethrough.
Dependencies are inferred from the claim text.