Pratt-whitney Canada Corp

United Technologies Corporation

David Frederick Glasspoole

Remy Synnott

Sami Girgis

Ricardo Trindade

Nicolas Grivas

Rene Paquet

Bruno Chatelois

John H Mosley

James P Chrisikos

Charles C Wu

Roger Gates

Alan Juneau

René Paquet

John J O'Connor

Yvan Schraenen

Francois Caron

François Caron

A cooling system for a gas turbine engine turbine section includes a rotor supporting a blade having a cooling passage. A disc is secured relative to the rotor and it forms a cavity between the rotor and the disc. A bleed air source is in fluid communication with the cavity. An impeller is arranged in the cavity. The impeller is configured to increase a fluid pressure within the cavity to drive bleed air from the bleed air source and thereby provide a pressurized cooling fluid to the cooling passage.

Gas turbine engine turbine impeller pressurization

A rotor retaining system for a rotor assembly of a gas turbine engine includes a washer interlocking multiple retaining nuts to prevent relative rotation. The retaining nuts retain a rotor disc and a cover plate in position, respectively. A wire is provided to retain the washer in position and which may dampen vibration during engine operation.

Turbine rotor retaining system

A balancing weight clip with a mass adapted to balance a rotor assembly of a gas turbine engine, includes a weight portion, a first flange engaging portion and a second flange engaging portion extending from the weight portion, each being engageable with a sidewall of at least one recess located on an edge of a flange of a disc of the rotor assembly. Each flange engaging portion is provided with a hook engageable with a mating groove provided on a face of the flange. At least one of the first and second flange engaging portions is resiliently biased so that the first and second flange engaging portions are elastically moveable away from one another to removably secure the balancing weight clip to the flange and engage each hook with the mating groove.

Radial balancing clip weight for rotor assembly

A retaining ring arrangement is provided for axially holding a component on a rotating component of a gas turbine engine. The retaining ring arrangement comprises a split retaining ring mounted in a circumferential groove defined in a radially outer surface of the rotating component. The inner diameter of the retaining ring is biased inwardly in radial contact with a radially outer facing seat provided on one of the two components to be assembled. An anti-rotation feature is provided at the inner diameter of the retaining ring for restraining the ring against rotation. A sleeve surrounds the retaining ring to limit radial expansion thereof when subject to centrifugal forces during engine operation.

Retaining ring arrangement for a rotary assembly

A balancing weight clip for balancing a rotor assembly of a gas turbine engine which includes a weight portion, and a first flange engaging portion and a second flange engaging portion extending from the weight portion. The weight portion and the first and second flange engaging portions define a flange receiving opening for receiving a flange of a disc of the rotor assembly. The first flange engaging portion is provided with a detent facing the second flange engaging portion and engageable with a mating groove provided on a face of the flange. At least one of the first and second flange engaging portions is elastically deformable so that the first and second flange engaging portions are elastically moveable away from one another to removably receive the flange in the flange receiving opening and engage the detent with the mating groove.

Axial balancing clip weight for rotor assembly and method for balancing a rotor assembly

Inlets are provided at a front end of inter-blade cavities for allowing coolant to flow therein to cool down the undersurface of the blade platforms as well as the rim of the disc of a rotor assembly.

Blade under platform pocket cooling

An exhaust mixer for a gas turbine engine including a plurality of circumferentially distributed alternating inner and outer lobes, where each of the inner lobes is configured with a circumferential offset between the base and the tip thereof, and a direction of the circumferential offset defined from the base to the tip of each of the inner lobes is the same for all of the inner lobes and opposite to that of a swirl component of a main gas path flow entering the exhaust mixer.

Deswirling exhaust mixer

A cooling device includes a plurality of passages extending through outer platforms of turbine vane segments for directing cooling air in a choked flow condition towards a downstream turbine shroud.

Shroud leading edge cooling

A simplified vane mounting arrangement by which a vane ring can be pre-assembled to an inner support ring before being installed in an outer casing.

Vane attachment arrangement

Gas flow is redirected by a feature disposed on a trailing edge of at least one segment of a peripheral gas path defining surface to improve alignment with a downstream portion of the gas path.

Gas turbine gas path contour

A Tangential On-Board Injection (TOBI) nozzle or a Radial On-Board Injection (ROBI) nozzle with adjustable flow area in a gas turbine engine for directing a cooling air flow into a rotor assembly of the turbine is disclosed. The TOBI or ROBI nozzle is a unitary cast structure including a plurality of tangentially angled cooling air passages, a number of the passages being cast-closed. After a flow test is conducted using the TOBI or ROBI nozzle, one or more of the cast-closed passages may be selectively machined open if the mass flow of the TOBI or ROBI nozzle does not satisfy the design point. Therefore, the structure of the TOBI or ROBI nozzle is easily fabricated using a casting process with low manufacturing costs while the optimum cooling air flow is achieved by adjusting the total flow area of the TOBI or ROBI nozzle before it is installed to the gas turbine engine. Furthermore, the TOBI or ROBI nozzle is advantageously supported in a cantilevered manner to avoid the thermal stress caused by temperature differential. The adjustable flow area feature also enables the TOBI or ROBI nozzle to be broadly used in different types of engines, the required mass flow of which are various.

Growing community of inventors

St. Lambert, Canada

David Frederick Glasspoole