Rolls-royce Corporation

Alan Richard Jones

John Richard Webster

Gary Eadon

Ian D Brown

Duncan Pollard

Gareth J Jones

Rodney D Greenough

There is disclosed an axial flow machine () comprising an annular flow path (); a stator ring () comprising a plurality of stators mounted at their radially outer ends and extending into the annular flow path (); a non-rotating body () axially adjacent the stator ring (); and an annular shroud () disposed between the radially inner end of the stator ring () and the body (). The shroud () is supported on the stator ring () and moveable relative the body (); and the shroud () cooperates with the body () to inhibit a flow through a clearance pathway () therebetween.

Axial flow machine

An edge detector is provided for determining the axial position of the leading or trailing edge of a rotating blade within rotating machinery. The edge detector includes a set of axially spaced tip detection probes locatable within a casing of the machinery. Each probe is arranged to detect whether or not the blade tip passes over that probe. The edge detector determines the axial position of the edge of the blade as the position of the boundary between those tip detection probes which detect passage of the blade tip thereover and those tip detection probes which detect no passage of the blade tip thereover.

Edge detector

A method of inhibiting ice accretion within a turbine engine, including the steps: (a) operating the turbine engine at a predetermined engine speed; and (b) driving the compressor of the turbine engine at an elevated speed which is greater than the nominal speed of the compressor at the predetermined engine speed so as to inhibit ice accretion within the compressor.

Method of inhibiting ice accretion within a turbine engine and control system therefor

A rotor () for a gas turbine engine () has a low emissivity surface finish, or high emissivity surface finish (), on at least a portion of its surface () to reduce temperature differentials between an upper portion and a lower portion of the rotor (). This reduces bowing of the rotor () to allow the gas turbine engine () to be started without harmful vibrations of the rotor ().

Gas turbine engine and a rotor for a gas turbine engine

A control arrangement () comprises a first selectable controller () for controlling an action, and a second selectable controller () for controlling the action. The arrangement also includes a selector () for selecting one of the controllers () to control the action. The arrangement () further includes a first heat exchanger () associated with the first controller () to effect a transfer of heat between the first controller () and the first heat exchanger (). The arrangement also includes a second heat exchanger () associated with the second controller () to effect a transfer of heat between the second controller () and the second heat exchanger ().

Control arrangement for cooling power electronic components

Apparatus for maintaining the temperature of a component of a gas turbine engine below a predetermined maximum working temperature comprises a reservoir for a cooling fluid having a boiling point below the working temperature and in which the component is immersed or with which it is in contact. At least two heat exchangers are associated with the reservoir and operable to effect condensation of vaporised cooling fluid and return of same to the reservoir. Preferably the apparatus is a closed system incorporating three heat exchangers respectively adapted to effect heat exchange with engine fuel, compressed air derived from a fan or low pressure compressor of the engine and ambient air. Means may advantageously be provided to ensure return of condensed cooling fluid to the reservoir when the attitude of the reservoir is altered as a result of aircraft maneuvers.

Cooling systems

Apparatus for maintaining the temperature of a component of a gas turbine engine below a predetermined maximum working temperature comprises a reservoir for a cooling fluid having a boiling point below the working temperature and in which the component is immersed or with which it is in contact. At least two heat exchangers are associated with the reservoir and operable to effect condensation of vaporized cooling fluid and return of same to the reservoir. Preferably the apparatus is a closed system incorporating three heat exchangers respectively adapted to effect heat exchange with engine fuel, compressed air derived from a fan or low pressure compressor of the engine and ambient air. Means may advantageously be provided to ensure return of condensed cooling fluid to the reservoir when the attitude of the reservoir is altered as a result of aircraft maneuvers.

A fluid flow control valve ( ) comprises a valve seat ( ) and a valve stem ( ) which is movable towards or away from the valve seat ( ) to control the fluid flow through the valve ( ). A magnetostrictive element ( ) is arranged to move the valve stem ( ) towards the valve seat ( ) and a spring ( ) is arranged to move the valve stem ( ) away from the valve seat ( ). A valve wall ( ) encloses the valve seat ( ), valve stem ( ), spring ( ) and magnetostrictive element ( ). A magnetic coil ( ), a keeper ( ) and a permanent magnet ( ) are arranged around the valve wall ( ). The fluid flow control valve ( ) is used to modulate the supply of fuel to a gas turbine engine combustion chamber to reduce combustion noise especially in premixed lean burn combustion chamber. The advantage is that there are no seals in the valve wall where leakage may occur and the valve is modular.

Fluid flow control valve

A rotor ( ) for a gas turbine engine ( ) has a low emissivity surface finish, or high emissivity surface finish ( ), on at least a portion of its surface ( ) to reduce temperature differentials between an upper portion and a lower portion of the rotor ( ). This reduces bowing of the rotor ( ) to allow the gas turbine engine ( ) to be started without harmful vibrations of the rotor ( ).

An apparatus for detecting pressure in a hollow fan blade of a turbofan gas turbine engine comprises a magnetostriction transducer arranged in a sub chamber of the fan blade which is interconnected to a main chamber. A magnetic coil is arranged in the fan casing of the turbofan remote from the fan blade, and an alternating current is supplied from a supply to the magnetic coil to produce an alternating magnetic field. The alternating magnetic field causes the magnetostriction transducer to generate vibrations in the fan blade and the magnetostriction transducer. A magnetic search coil detects changes in the magnetic field, which corresponds to the vibrations, and a processor analyses the vibrations to determine if there has been a change in the resonant frequency of the vibrations which is indicative of a change in the pressure in the fan blade. The processor supplies a signal to a display or to an alarm. The change in the pressure is indicative that the fan blade is cracked and needs replacing.

Method and apparatus for remotely detecting pressure, force, temperature, density, vibration, viscosity and speed of sound in a fluid

An apparatus (42) for inspecting an as cast turbine blade (40), with impingement cooling passages (36) (see FIG. 2 ), comprises a vacuum pump (52) arranged to evacuate the interior of the turbine blade (40) through pipe (48) and valve (54) and a supply of steam (46) arranged to supply steam to the interior of the turbine blade (40) through the pipe (48) and a valve (50). An infrared camera (56) is arranged to view the outer surface (32) of the turbine blade (40) to detect hot spots produced on the outer surface (32) of the turbine blade (40) by jets of steam impinging on the inner surface (35) of the turbine blade (40) from the cooling passages (36). A processor (60) records the images produced by the camera (56) and analyses the images to determine if the cooling passages (36) have been formed and if they have been formed in the correct position.

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Derby, United Kingdom

Alan Richard Jones