Cooling flow side entry for cooled turbine blading
This patent describes a gas turbine engine is described comprising: a turbine rotor having a central hub section extending radially from an axially extending central bore to an outer periphery, and turbine blades secured to the outer periphery and disposed circumferentially therearound, the blades having internal cooling passages opening onto the outer periphery of the hub sections; the hub section comprised of permanently intersecured elements configured and relatively arranged to define a radially extending internal cavity means within the hub section opening onto the periphery thereof for delivering cooling fluid flow to the internal cooling passages of the blades; at least one of the elements defining a pair of axially extending, radially spaced circular walls on an external surface of the hub section radially intermediate the central bore and the outer periphery to present a continuous annular channel disposed between the pair of walls and concentric with the bore. The hub section configured whereby the annular channel opens into the internal cavity means; rotary shaft means disposed in the central bore in torque transfer interengagement with the hub section; annular stationary nozzle means extending into the continuous annular channel for delivering cooling fluid flow thereinto. The internal cavity means extending radially from the channel to the outer periphery, and further defining inward passages extending radially inwardly from the channel to open into the central bore.
- Assignee:
- Allied-Signal Inc., Morris Township, Morris County, NJ
- Patent Number(s):
- US 4759688
- OSTI ID:
- 6528563
- Resource Relation:
- Patent File Date: Filed date 16 Dec 1986
- Country of Publication:
- United States
- Language:
- English
Similar Records
Over the shaft fuel pumping system
Turbine vane assembly with integrally cast cooling fluid nozzle