Rolls-royce Corporation

Rolls-royce North American Technologies Inc.

Bradford John Riehle

Brandon R Snyder

Michael R Whitten

James Sellhorn

James Carl Loebig

John Alan Weaver

Chadd D Engel

John Weaver

Chadd Engel

James E Sellhorn

A retaining collar is disclosed for a bayonet mount comprising a rotor disc having a male mounting member defining a pair of apertures and an auxiliary annular wheel defining a plurality of mounting slots. The retaining collar comprises a ring-shaped body and a pair of retention pins. The ring-shaped body has a pair of circumferential end portions separated by a circumferential gap, and an arcuate radial outer surface extending circumferentially between the end portions. The body is dimensioned so that the radial outer surface frictionally engages a radial inner surface of a cylindrical male mounting member in the bayonet mount. The pair of retention pins each extend radially outward from one of the circumferential end portions. Each of the retention pins are dimensioned to extend radially outward from the body through one of said apertures and one of said mounting slots.

Turbine rotor assembly having a retaining collar for a bayonet mount

A gas turbine engine comprises an engine core, a tie bolt, and a fail-safe system. The engine core includes a compressor, a turbine, and a shaft that couples the compressor with the turbine for rotation with the turbine about an axis. The tie bolt locates axially the compressor relative to the turbine. The fail-safe system is configured to transmit torque from the turbine to the compressor through the tie bolt in response to a shaft disconnect event.

Gas turbine engine with fail-safe shaft scheme

Various embodiments of the present application provide one or more of: (1) auxiliary wheel that (a) enables accurate speed detection of a turbine disc and/or (b) presents a machining surface for balance correction; and/or (2) techniques for mounting an auxiliary wheel to a rotor, such as a turbine disc.

Turbine assembly with auxiliary wheel

A vane adapted for use in a gas turbine engine includes a forward following serpentine cooling path having a plurality of divider walls to direct cooling airflow. The serpentine cooling path optionally includes one or more bifurcating walls in the cooling path to split the airflow. The serpentine cooling path is in communication with an aft inlet in the vane and air passing through the serpentine cooling path exits a forward outlet in the vane into a forward rotor/stator cavity.

Forward flowing serpentine vane

Disclosed herein are examples of gas turbine engines and assemblies of combustors and turbine nozzles for such gas turbine engines. The combustor wall includes an inner wall, an outer wall, and an upstream dome. The combustor outer wall and/or inner wall may comprise of a plurality of combustor cassettes. A turbine nozzle is defined by an inner nozzle shroud and an outer nozzle shroud. An inner edge of a ring mount is coupled to both of the downstream end of the outer wall and the nozzle upstream end of the outer nozzle shroud, and an outer edge of the ring mount is coupled to the outer casing, such as, for example, by a mounting stake.

Combustor cassette liner mounting assembly

An improved system, apparatus and method for intercooling a turbo fan engine, and more specifically, a system for intercooling a turbo fan engine employing a secondary bypass duct that minimizes pressure losses. The secondary bypass duct is radially inwardly disposed from a fan bypass duct and receives fan bypass air through an inlet. The portion of fan bypass air flows through one or more microchannel or minichannel heat exchangers. The secondary bypass duct has an outlet in communication with the bypass air stream downstream of the throat of a fan bypass nozzle. The secondary bypass air is accelerated at the exit to create thrust.

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Plainfield, IN, United States of America

Bradford John Riehle