Rolls-Royce Corporation

Colin Young

Guy David Snowsill

Timothy John Scanlon

Roderick M Townes

Alan Robert Maguire

Paul William Ferra

Leo Vivian Lewis

Paul J Wilson

Changmin Son

Clive Peter Gravett

Lou Peng

Martin Berthold

Timothy John Scanlan

A planetary gearbox having a sun gear, a plurality of planet gears, a ring gear, and a plurality of journal bearing pins. At its axially forward face side and/or at its axially rearward face side, each planet gear forms a recess that extends inside the planet gear starting from the face side. The planet gear forms a protrusion at its axially forward face side and/or at its axially rearward face side. The protrusion has an axial extent and a radial extent, wherein the radial extent is limited at the respective face side to the area between the planet gear inner bore and the radial inner limit of the respective recess in the planet gear, and wherein the protrusion is configured to provide for a flow path for oil emerging from the journal bearing that guides the oil away from the journal bearing.

Planetary gearbox

A hydraulic seal arrangement for a rotating machine comprises an annular housing disposed around a shaft having an axis of rotation, the annular housing being relatively rotatable with respect to the shaft and having a sealing fluid zone within a radially outer portion of an interior of the annular housing. A fin extends radially from the shaft into the annular housing, with at least a portion of the fin extending radially into the sealing fluid zone. In use, the sealing fluid is centrifugally accelerated before being directly introduced into the sealing fluid zone by a sealing fluid inlet so as to generate a swirl component upon its introduction.

Hydraulic seal arrangement

A gas turbine engine rotor arrangement comprising at least one blade and a disc is disclosed. The blade extends radially outwards from the disc and is secured thereto by cooperating shank of the blade and recess of the disc. The shank comprises a bottom surface facing a base surface of the recess, the bottom surface having axially extending peripheral edges. The bottom surface is shaped so that when the engine rotor arrangement is in use, liquid in a cavity between the bottom surface and base surface, acted upon by an unbalanced force in the radially outward direction, is guided by the bottom surface to flow between and away from the axial edges.

Gas turbine engine rotor arrangement

This invention concerns a system for cooling components in a gas turbine engine, the gas turbine engine including a compressor for driving a primary gas flow to a combustor and a turbine arranged to be driven by combustion gases from the combustor, wherein the system includes: an annular cooling flow passage arranged for fluid communication between the compressor and the turbine, the flow passage having a first inlet arranged to receive gas from the primary gas flow downstream of compressor, and a second inlet located upstream of the first inlet, wherein the annular cooling flow passage has at least one internal wall for guiding airflow from the first inlet towards the airflow from the second inlet, the airflow from the first and second inlets coalesce within the annular flow passage prior to passing along the passage in a direction from the compressor to the turbine.

Axial flow machine cooling system

Flow restrictors (), () are widely utilized with regard to providing flow control in such situations as with respect to sealing and pressurization of bearing chambers in gas turbine engines. The restrictor (), () restricts a flow (), () but with prior arrangements may be susceptible to deposition upon flank surfaces of the restrictor (). These depositions may fragment and block an aperture (), () of the restrictor (), () reducing operational effectiveness. By provision of a deflector () having a deflector surface () flows () can be presented such that a greater proportion of the flow including droplets or other matter which may result in surface deposition or erosion will pass directly through an aperture () rather than impinge upon the flank surfaces of the restrictor (). Furthermore, the deflector () is dimensioned such that surfaces which may be susceptible to deposition have dimensions smaller than the aperture ().

Flow control arrangement

A gas turbine engine comprising a rotor and a stator which define first, second and third cavities; the rotor and stator define a seal therebetween and which is located for sealing between the second and third cavities, the rotor comprises an aperture through which a gas flow passes from the first cavity to the second cavity characterized in that the seal comprises a deflector that extends axially over at least a portion of the aperture to deflect at least a part of the gas towards the rotor.

Turbine apparatus

It is known with regard to particularly cavities below high pressure turbine discs that mixing of hot gas leakage flows through an inner seal with cooling flows can diminish the effectiveness of that cooling flow when presented to other parts for cooling. By providing a path within a wall which is particularly shaped in portions it is possible to provide entrainment of a hot leakage gas flow away from entry into the cavity. Thus, the cooling flow retains a higher cooling effect and maintains its swirling nature in comparison with prior arrangements where mixing with the hot leakage flow occurred.

Flow cavity arrangement

A rotor assembly for a gas turbine engine, the rotor assembly comprises at least two rotors defining a cavity therebetween. A first rotor defines a cooling air inlet in its radially inward portion. A second rotor defines a cooling air outlet in its radially outward portion, such that the cooling air passes radially outwardly through the cavity.

Gas turbine engine rotor ventilation arrangement

A cooling arrangement comprises a support () for a plurality of blades (). The support () comprises a plurality of blade mounting members () provided between adjacent blades (). The blades () are mounted upon the blade mounting members (). The cooling arrangement defines a pathway () for a cooling fluid. The cooling arrangement further includes a fluid directing formation (A) to direct the cooling fluid across the blade mounting member ().

Growing community of inventors

Derby, United Kingdom

Colin Young