Accession Number : ADD009336

Title :   Multiple Compartment Spring-Loaded Inserts for Cooling a Turbine Blade Airfoil.

Descriptive Note : Patent Application,

Corporate Author : DEPARTMENT OF THE AIR FORCE WASHINGTON DC

Personal Author(s) : Haubert,Richard

Report Date : 13 Jan 1982

Pagination or Media Count : 17

Abstract : An airfoil of a turbine blade or the like has a pair of inserts positioned therein for causing impingement of cooling air flow axially along the internal surfaces of the airfoil walls. The inserts each have longitudinally-extending radial ribs and transversely-extending cross ribs which intersect and form compartments. Selected contiguous compartments are interconnected by passages in the radial ribs for cooling air flow therethrough in several successive steps so as to tailor the pattern of cooling of the walls to the particular pressure gradient existing along the airfoil. Also, resilient springs are provided between the inserts for loading them against the airfoil walls. Also, wear pads are located at the regions of contact between the inserts and the airfoil walls. (Author)

Descriptors :   *Patent applications, *Gas turbine blades, *Axial flow turbine rotors, *Gas turbines, *Cooling, Axial flow, Control systems, Combustion chamber liners, Airfoils, Patterns, Inserts, Air flow, Springs, Ribs, Flexible structures, Compartments, Walls, Internal, Coatings, Thermal degradation, Pressure gradients

Subject Categories : Hydraulic and Pneumatic Equipment
      Jet and Gas Turbine Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE