Cummins Inc.

Simon David Moore

Matthew William Edwards

John Frederick Parker

James Alexander McEwen

Robert L Holroyd

Tom J Roberts

Stephen E Garrett

Stephen David Hughes

Tim Denholm

Christopher Normington

Michael Voong

Arun Vijayakumar

Karl Conlon

Nandakishore Arcot Madhusudan

Mark R Holden

George E Sandford

Christopher Parry

Christopher J Shaw

Paul Ghosh

Andrew Sullivan

James Alexander Mcewen

Ali Sophian

Ian Higgins

George E Sanford

A pin member is proposed for a turbo-machine having a shroud arranged to rotate within a turbine housing. The pin member is configured to limit this rotation. It is a one-piece element comprising a cylindrical body and a limit surface for opposing motion of the shroud.

Pin member for turbine

A turbine for a turbo-machine is proposed in which, at a gas inlet for a turbine wheel, vanes extend from a nozzle ring though slots in a shroud. The nozzle ring and shroud are relatively rotatable about a rotational axis of the turbine by at least 0.1 degrees. In use, the nozzle ring and shroud are relatively rotated to bring one side of the vane into close contact with one surface of the slot, to inhibit leakage of gas between the vane and the slot surface. For this purpose the respective surfaces of the nozzle and slot can be configured to closely conform to each other. If there is differential thermal expansion of the shroud and nozzle ring, the nozzle ring and shroud can relatively rotate, to withdraw the vane from the edge of the slot to relieve the pressure between them.

Vanes and shrouds for a turbo-machine

A turbine for a turbo-machine is proposed in which, at a gas inlet, vanes, extending from a nozzle ring though slots in a shroud, are shaped on one side to as to substantially conform to the profile of the surface of the slot, whereby a close connection can be formed between the vane and the slot to inhibit leakage of gas between the vane and the slot surface.

Vane arrangement for a turbo-machine

A variable geometry turbine comprising a turbine wheel mounted for rotation about a turbine axis within a housing. The housing defines an annular inlet surrounding the turbine wheel and defined between first and second inlet sidewalls. The turbine further comprises a cylindrical sleeve that is axially movable across the annular inlet to vary the size of a gas flow path through the inlet. The annular inlet is divided into at least two axially offset inlet passages. The inner diameter of the sleeve is greater than the inner diameter of the inlet passages.

Turbomachine

A variable geometry turbine has annular inlet passageway defined between a first surface of a radial wall of a movable wall mounted within a cavity and a facing wall of the turbine housing. The radial wall defines a second surface that opposes the first surface. The moveable wall member comprises an annular flange that extends axially into the cavity and supports a radial flange defining opposing third and fourth surfaces. The radial flange seals against an annular sleeve in the cavity to define a first area within the cavity which includes the radial second and third surfaces and a second area within the cavity which includes the radial fourth surface. The first and second areas are in fluid communication with regions of the annular inlet passageway which are respectively upstream and downstream of a radial vane passage.

Variable geometry turbine

According to an aspect of the invention, there is provided a variable geometry turbine comprising: a turbine wheel mounted for rotation about a turbine axis within a housing, the housing defining an annular inlet surrounding the turbine wheel and defined between first and second inlet sidewalls; and a cylindrical sleeve axially movable across the annular inlet to vary the size of a gas flow path through the annular inlet, the annular inlet being divided into at least two axially offset inlet portions; and a ring-like seal adjacent a free end of the sleeve, at least a part of the ring-like seal being located in-between the sleeve and the inlet portions, or a structure defining the inlet portions.

Variable geometry turbine seal

A variable geometry turbine comprises a turbine wheel mounted for rotation about a turbine axis within a housing, the housing defining an annular inlet surrounding the turbine wheel and defined between first and second inlet sidewalls; and a cylindrical sleeve axially movable across the annular inlet to vary the size of a gas flow path through the inlet; wherein the annular inlet is divided into at least three axially offset annular inlet portions by two or more axially spaced annular baffles disposed between the first and second inlet sidewalls; inlet vanes extending axially into at least one of the inlet portions and defining circumferentially adjacent inlet passages; and wherein each of at least two of said baffles extends radially inboard of inlet vanes which extend into at least one of the inlet portions axially adjacent the respective baffle, and wherein a distance between an inner diameter of a first baffle of said at least two of said baffles and a trailing edge of a radially innermost vane in one of said annular inlet portions adjacent the first baffle is greater than a distance between an inner diameter of a second baffle of said at least two of said baffles and a trailing edge of a radially innermost vane in one of said annular inlet portions adjacent the second baffle.

Growing community of inventors

Huddersfield, United Kingdom

Simon David Moore