General Electric Company

Richard H Andersen

Robert J Corsmeier

William A Litzinger

Dean Thomas Lenahan

Frederick C Herzner

James P Rauf

Carl R Dins

Means for securing a member, such as a blade retainer, to a structure, such as a disc. An annular, preferably split, retaining ring is disposed in a recess of the disc and is shaped to receive a part of the blade retainer which is also disposed within the recess thereby securing the blade retainer to the disc. A method of securing the blade retainer to the disc is also provided and includes the steps of inserting the retaining ring into the recess and compressing the ring, inserting a part of the blade retainer into the recess and deflecting it axially, and releasing the retaining ring from compression and the blade retainer from deflection.

Means and method for securing a member to a structure

A turbomachinery rotor blade includes an internal coolant cavity between a pair of radially extending side walls which combine to form an airfoil having an open end between the radial extremities of the side walls. A tip cap recessed within the open end partially seals the internal coolant cavity from the blade environment. The radial extremities of the side walls extending beyond the tip cap into proximity with a circumscribing shroud form a labyrinth seal for inhibiting leakage of the operating gas across the blade tip. A portion of the cooling air is routed from the internal coolant cavity, around the tip cap and through a multiplicity of generally radial channels formed within the radial extremities of the side walls to provide cooling thereof, and is thereafter discharged out of the open end of each channel at the tip of the side walls.

Tip cooling for turbine blades

A gas turbine engine having a compressor and an air-cooled turbine is provided with a cooling system for decreasing the temperature of the turbine cooling air. A compact heat exchanger, rotatable with the compressor, receives a portion of the pressurized air which is bled from the compressor. Relatively cool engine lubrication oil is pumped through the heat exchanger into heat exchange relationship with the pressurized air, thereby cooling the air and heating the lubrication oil. The cooled air is then routed to and circulated through the turbine blades to provide improved internal cooling thereof. The heated lubrication oil is collected from the heat exchanger and routed to a second heat exchanger wherein it is placed in heat exchange relationship with engine fuel to recover the heat extracted from the compressor bleed air and to return the heat to the engine operating cycle. The cooling system is designed to contain the lubricant in the unlikely event of a leak developing in the heat exchanger. Incorporation of the heat exchanger of the present invention into a gas turbine engine permits a reduction in the quantity of compressor air required for turbine rotor blade cooling and, thus, provides an improvement in engine performance.

Cooling air cooler for a gas turbine engine

A hollow turbomachinery blade is formed by way of casting or the like with an open tip end except for a bridge which is formed integrally with the blade side walls at a central position with respect to the leading and trailing edges. Also formed integrally with the blade side walls, proximate the tip end openings near the leading and trailing edges, are a plurality of supporting and retaining bosses, the supporting bosses being in substantially the same plane as the cast cap, and the retaining bosses being disposed radially outward thereof. Each of the forward and rear tip caps is installed by placing it over the bridge ad then sliding it either forward or rearward to be captured by the supporting and retaining bosses and to thereby close the respective tip opening. Each of the tip caps is then brazed into position so as not to allow its sliding back out.

Tip cap apparatus and method of installation

A bore vane assembly is adapted to be received within the annular passage formed between two axially displaced turbine disc halves so as to provide axial columnar support therebetween during high centrifugal loading. The bore vane assembly includes a plurality of axially extending vanes which provide the required support and which also serve to pump cooling fluid from a plenum into the turbine disc.

Bore vane assembly for use with turbine discs having bore entry cooling

A hollow turbomachinery blade is formed by way of casting or the like with an open tip end except for a bridge which is formed integrally with the blade side walls at a central position with respect to the leading and trailing edges. Also formed integrally with the blade side walls, proximate the tip end openings near the leading and trailing edges, are a plurality of supporting and retaining bosses, the supporting bosses being in substantially the same plane as the bridge, and the retaining bosses being disposed radially outward thereof. Each of the forward and rear tip caps is installed by placing it over the bridge and then sliding it either forward or rearward to be captured by the supporting and retaining bosses and to thereby close the respective tip opening. Each of the tip caps is then brazed into position so as not to allow its sliding back out.

Growing community of inventors

Cincinnati, OH, United States of America

Richard H Andersen