Rolls-royce Corporation

Julian Glyn Balsdon

Simon James Jones

Sean Alan Walters

Reza Manzoori

Rupert John Taylor

Rupert J Taylor

Simon Jones

A distributor device for distributing cooling air within a gas turbine engine, the device including a base mountable adjacent an inlet for air to be distributed; and a deflector supported by the base and in fluid communication with the air inlet, the deflector being configured to direct air from the air inlet in a plurality of directions within the engine; wherein the deflector includes one or more deflecting surfaces curvilinearly configured to direct the air differentially in a plurality of desired directions within the engine. In embodiments the deflecting surface(s) is/are curved and are so configured such that air from the air inlet is directable either: (i) in directions of travel in each of a plurality of desired different, non-parallel directions within the engine; or (ii) in each of a plurality of desired different directions within the engine with different flow rates.

Distributor device for cooling air within an engine

A seal segment of a shroud arrangement for bounding a hot gas flow path within a gas turbine engine is described. The seal segment is upstream of a second component of the gas turbine engine relative to the hot gas flow path. The seal segment comprises: a plate having: a downstream trailing edge; an inboard side which faces the hot gas flow path when in use; an outboard side; and a first part of a two part seal attached on the outboard side, wherein a second part of the two part seal is attached to the second component such that in an assembled gas turbine engine the two part seal provides an isolation chamber which is in fluid communication with the hot gas flow path via the trailing edge of the plate. A gas turbine having the seal segment is also described.

Dual source cooling air shroud arrangement for a gas turbine engine

A pressure actuated tip clearance system for a shroud structure of a gas turbine engine rotary stage includes an annular plenum chamber formed between an annular arrangement of a plurality of shroud liners on the inner circumference of the chamber and a generally cylindrical casing on the radially outer side, and, in use, a hot gas stream radially inwards of the shroud liners. Each shroud liner comprises a hollow box section comprising upstream and downstream walls, radially inner and outer walls, and side walls, the downstream and radially inner and outer walls being closed, the upstream wall having an air inlet aperture, and at least one of the side walls having at least one outlet aperture. The inlet aperture is in flow communication with a source of high pressure air at a pressure higher than that of the gas stream.

Blade tip clearance system

A sealing arrangement between annular components, for example in a gas turbine engine, comprises an L-shaped sealing ring. The sealing ringhas a first limbreceived in a groovein the first component, and a second limbhaving a sealing facewhich is maintained in contact with an abutment surfaceon the second componentunder the resilient action of the sealing ring. The second limbis exposed to the pressure in a chamberwhich assists the resilience of the sealing ringin maintaining sealing contact between the sealing faceand the abutment surface. Bleed holesare provided.

Sealing arrangement

A casing arrangement () for surrounding a rotary component () of a gas turbine engine () especially a turbine is disclosed. The arrangement () comprises an annular casing member (A) surrounding a bladed rotary section, such as a turbine stage. An array of gas path liner segments are suspended from the casing at a nominal clearance gap form the tips of the rotary blades. Running clearance is determined by expansion and contraction of the casing which, in turn, is controlled by a supply of heat transfer fluid passed through heat transfer holes in the casing. The casing arrangement described includes a passive pressure bleed effective during engine deceleration to reduce a pressure differential driving the fluid flow in order to avoid too rapid contraction of the casing as a result of overcooling.

Casing arrangement

A sealing arrangement that can be employed to maintain a seal in any suitable pressure vessel including but not limited to a gas turbine engine. The sealing arrangement is forg sealing a leakage gap between at least two relatively moveable parts that are adjacent to each other in a flow path between a region of high fluid pressure and a region of low fluid pressure. The sealing arrangement comprises at least two resilient sealing strips, each strip having a portion formed along at least part of its width to locate in a groove provided along adjacent faces of the relatively moveable parts. The remaining portion of each of the sealing strips has a substantially flat surface which, in operation, abuts a corresponding flat surface of an adjacent sealing strip, thereby forming a seal.

An annular seal plate for an interstage air riding seal arrangement for the internal cooling system of a gas turbine engine is mounted on a rotatable disc by means of an annular mortise and tenon mounting. The contact faces of the mortise and tenon are angled relative to a radial plane of the disc so that centrifugally generated forces are reacted by the faces in a sense to counter axial tilt so that a seal face of the plate lies exactly in a radial plane, at a design rotational speed, thereby to eliminate convergence or divergence between the seal faces of the air riding seal.

Seal plate

A vectorable nozzle mounting for an engine installation in a VSTOL aircraft in which hot gas nozzles are mounted on the airframe is described. A swivelable nozzle is mounted by means of a bearing on an intermediate fixed member such as a mounting ring on the airframe. The hot exhaust gas is discharged into the nozzle through a stub duct carried by the engine casing. Misalignment and movement between the duct and the nozzle is accommodated by movable sealing rings carried in the intermediate member which engage the outer surface of the duct. The sealing rings are spaced apart to form an annular chamber which is supplied with cooling air at a higher pressure than the pressure in the exhaust duct. The cooling air is arranged to cool the nozzle bearing and leakage passed the seals is of cooling air into the nozzle thus excluding hot exhaust gas from the engine bay.

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Bristol, United Kingdom

Julian Glyn Balsdon