Rolls-Royce Corporation

Timothy John Scanlon

Alan Robert Maguire

Leo Vivian Lewis

Guy David Snowsill

Colin Young

Marko Bacic

Paul William Ferra

John R Tippetts

Ronald William Daniel

Paul J Wilson

Geoffrey H Priestman

Luis F Llano

Jeffrey Alison Dixon

Paul A Sellers

Ivan Lars Brunton

John Russell Tippetts

Paul Wilson

Geoffrey Hugh Priestman

A gas turbine engine has a core engine including: a compressor, combustion equipment which receives compressed air from the compressor, a circumferential row of nozzle guide vanes, and a turbine. The nozzle guide vanes defines a throat receiving hot working gases from the combustion equipment into the turbine. The gas turbine engine further has an air system which is switchably operable between an on-position which opens a diversion pathway along which a portion of the compressed air exiting the compressor bypasses the combustion equipment to join the hot working gases at re-entry holes located between the nozzle guide vanes and a rotor at the front of the turbine, thereby increasing the semi-dimensional mass flow &#x3c9;(T30)/(P30) of the core engine at the exit of the compressor, and an off-position which closes the diversion pathway, thereby decreasing the semi-dimensional mass flow of the core engine at the exit of the compressor.

Gas turbine engine with diversion pathway and semi-dimensional mass flow control

A gas turbine engine includes a turbine and a turbine cooling arrangement. The turbine includes a turbine rotor surrounded by a static rotor track liner, and a nozzle guide vane downstream of the rotor in a core main gas flow path. The cooling arrangement includes a first air duct that provides cooling airflow to a rotor track liner cooling plenum and a second air duct that provides a cooling airflow to the nozzle guide vane. A common manifold is upstream in the cooling airflow of the ducts and provides cooling air to the ducts. A two-way valve modulates air provided to the ducts from the manifold. The valve is operates in a first or second mode. In the first mode, air flow to the first duct is relatively high and airflow to the second duct is relatively low compared to where the valve is operated in the second mode.

Gas turbine engine turbine cooling system

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

A clearance control device including a segment having a passage to deliver fluid towards a component rotating past the segment. Also a fluid flow device having a first fluid path coupled to the passage and a second fluid path that is decoupled from the passage. A first plasma generator is located in the fluid flow device that directs fluid towards the first fluid path; a second plasma generator is located in the fluid flow device that directs fluid towards the second fluid path; and a control arrangement is configured to alternately energize the first and second plasma generators at an energizing frequency to deliver fluid to the passage at a frequency coincident with the passing frequency of the component.

Clearance control

The present disclosure relates to a vortex reducer () for a bleed flow () in an axial turbomachine comprising a rotor disc (). The vortex reducer may comprise one or more guide channels () arrangeable adjacent to a first side () of the rotor disc to at least partially de-swirl the bleed flow. The vortex reducer may further comprise a passage () connecting the first side of the rotor disc to a high pressure flow source capable of providing flow () to the first side of the rotor disc to mix with the bleed flow on the first side of the rotor disc.

Vortex reducer

A gas turbine engine has in flow series a compressor section, a combustor, and a turbine section. The engine includes a turbine section rotor disc, and a stationary wall forward of a front face or rearward of a rear face of the rotor disc. The wall defines a cavity between the stationary wall and the rotor disc, and has a plurality of air entry nozzles through which cooling air can be delivered into the cavity at an inlet swirl angle. The engine further includes a cooling air supply arrangement which accepts a flow of compressed air and supplies the compressed air to the nozzles for delivery into the cavity. The cooling air supply arrangement and the nozzles are configured such that the inlet swirl angle of the air delivered into the cavity can be varied between a first inlet swirl angle and a second inlet swirl angle.

Gas turbine engine swirled cooling air

Provision of flow control arrangements which can be switched from high flow restriction to low flow restriction or vice versa are desirable. It is known to use switched vortex valves comprising a vortex chamber having a diverter portion which jets a through flow into either radial presentation to an outlet or tangential presentation with differential flow restrictions. Typically deflection is through cross flows presented from control ports as determined by mechanically actuated and controlled valves. Sensors are required to determine pressure differentials in order to actuate these moving part valves. By providing association between the control ports and an outlet path along with appropriate configuration and sizing of the flow regulators switching states can be provided through the cross flows presented via the flow regulators between the high and low through flow restriction. The flow regulators generally comprise orifice restrictors, diffusers/venturi arrangements or vortex throttles.

Flow control arrangement

Loss reduction apparatus for a fluid transfer system includes a fluid device. The fluid device defines a first fluid path along which a greater part of a fluid flows in a first condition, and a second fluid path along which a greater part of the fluid flows in a second condition. The apparatus is arranged so that when a leak occurs at a location in the system, the leak causes a relative reduction in fluid pressure at the location, which moves the device from the first condition to the second condition.

Loss reduction apparatus

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 flow control system comprises includes a fluidic control device having a main fluid path for a flow of fluid through the device, and a control fluid path for a control flow of fluid through the device. At least part of the control fluid path coincides with at least part of the main fluid path to control the flow of fluid out of the fluidic control device. A valve is associated with the control fluid path. The valve is movable between an open condition to allow fluid to flow along the control fluid path to effect the aforesaid control of the fluid flow out of the fluidic control device, and a closed condition to inhibit or prevent fluid flow along the control fluid path.

Flow control systems

It is known there is ingestion of hot gas flowfrom an annular flowin gas turbine engines. This flowis prevented from attaching to the disc by coolant flowpassing through gaps in lock platesby creation of a barrier layer. In order to regulate and enhance this effect spacer protrusionsare provided between ends of lock plates. In such circumstances the gapis controlled and therefore the rate of leakage flowregulated for best cooling effect. This cooling effect and cooling flowcan be further enhanced by providing chutesfor presentation of the coolant flow

Turbine engine cooling

A seal arrangementbetween a turbine shroud seal segmentsin a gas turbine engine. The arrangementcomprises facing slotsprovided respectively in the segmentswith offset spacesprovided between the segments. A stripis cemented into the slotsuch that the flow pathpasses through the space, around the free end of the strip, and out through the offset space, thereby providing a longer flow path.

Growing community of inventors

Derby, United Kingdom

Timothy John Scanlon