Mtu Aero Engines Ag

United Technologies Corporation

Mtu Aero Engines Gmbh

Mtu Motoren-und Turbinen-union Munchen Gmbh

Mtu Motoren-und Turbinen-union Muenchen, Gmbh

Georg Zotz

Werner Humhauser

Nicholas R Leslie

Stefan Beichl

Lothar Albers

Vitalis Mairhanser

Christian Greune

Fadi S Maalouf

Berthold Burgmeier

Harsimar Sahota

Giovanni Brignole

Helmut Gross

Rudolf Pilzweger

Hermann Becker

Giovanni Dr Brignole

Harsimar Dr Sahota

Stephan Pröstler

An inner ring according to the invention for a guide vane cascade of a turbomachine has a radially outer inner ring surface as well as a plurality of bearing mounts for a respective guide vane plate of a guide vane. The bearing mounts each have an opening in the outer inner ring surface as well as a bottom face lying radially opposite the opening. At least two of the bearing mounts are separated from each other by a separating wall and are connected to each other in a region of their bottom face by a through-opening. A guide vane cascade according to the invention for a turbomachine has an inner ring according to the invention and a plurality of guide vanes inserted into the bearing mounts.

Inner ring and guide vane cascade for a turbomachine

The invention relates to an inner ring system for an inlet guide vane cascade of a turbomachine. The inner ring system comprises an intermediate casing for accommodating structural loads and an inner ring, which is divided axially into a first ring segment and a second ring segment, which together form recesses for bearing radially inner end portions of guide vanes of the inlet guide vane cascade, wherein at least the second ring segment is fixed in place on the intermediate casing by screw connection. The invention further relates to an inner ring and to an intermediate casing for such an inner ring system, as well as a turbomachine that has such an inner ring system.

Inner ring system for an inlet guide vane cascade of a turbomachine

A blade outer air seal (BOAS) for a gas turbine engine includes, among other things, a seal body having a radially inner face and a radially outer face that axially extend between a leading edge portion and a trailing edge portion. The BOAS includes a trough disposed on the radially inner face and an abradable seal received within the trough. The trough is open to expose a leading edge of the abradable seal to a core flow path of the gas turbine engine.

Blade outer air seal for a gas turbine engine

A turbomachine having at least one circulation structure is disclosed. The circulation structure has an annular space with baffle elements surrounding a main flow path and is open to the main flow path. A housing of the turbomachine to receive the circulation structure is divided in an axial plane into a front housing region and a rear housing region and the circulation structure is divided into a front structure region and a rear structure region in the axial plane of separation. A circulation structure divided into two parts in the axial direction and a method for the same is also disclosed.

Turbomachine, circulation structure and method

The present invention provides a split inner ring for an adjustable guide blade arrangement, having a ring segment arrangement with at least two ring segments () and a bearing bush arrangement with at least one bearing bush () for mounting an adjustable guide blade () of the guide blade arrangement, in which a ring segment and another ring segment of the ring segment arrangement can be joined together by the bearing bush arrangement.

Split inner ring

A guide vane for a turbomachine axially pivotably coupled to a radially outwardly disposed flow-limiting wall and to a radially inwardly disposed inner ring of the turbomachine; and a trailing edge gap being formed between an upper trailing edge of the guide vane and the flow-limiting wall and/or between a lower trailing edge of the guide vane and the inner ring; the upper trailing edge and/or the lower trailing edge of the guide vane having at least one air outlet opening for an air outflow for forming an air curtain for at least partially sealing the trailing edge gap in the area of the upper trailing edge and/or the lower trailing edge in the area of the lower trailing edge. Also, a guide vane cascade, as well as a method for manufacturing a guide vane or a guide vane cascade.

Guide vane for a turbomachine, guide vane cascade, and method for manufacturing a guide vane or a guide vane cascade

A blade outer air seal (BOAS) for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a seal body having a radially inner face and a radially outer face that axially extend between a leading edge portion and a trailing edge portion. The BOAS includes a trough disposed on the radially inner face and an abradable seal received within the trough. The trough is open to expose a leading edge of the abradable seal to a core flow path of the gas turbine engine.

An inner ring of a fluid flow machine includes fixing rings and seal carriers split into at least two fixing ring segments and into at least two seal carrier segments, respectively. The fixing ring segments and the seal carrier segments are arranged with the respective end faces facing each other. A first fixing ring segment has a first ring segment shoulder and a second fixing ring segment has an offset second ring segment shoulder. A first seal carrier segment has a first carrier segment shoulder, and a second seal carrier segment has a second carrier segment shoulder, which is offset with respect to the first carrier segment shoulder. In a separation plane of the inner ring, the first carrier segment shoulder abuts the second ring segment shoulder at the end face. Also in the separation plane, the second carrier segment shoulder abuts the first ring segment shoulder at the end face.

Inner ring of a fluid flow machine and stator vane array

A device for the adjustment of stator vanes of a turbo engine includes an adjusting ring and an adjusting lever. The adjusting lever includes a first end, and a second end having an opening. The first end of the adjusting lever is connected to the adjusting ring. The device also includes an end of a shank of the stator vane, and the end of a shank of the stator vane enters into the opening of the second end of the adjusting lever to connect the second end of the adjusting lever to the end of the shank of the stator vane. The adjusting lever swivelingly connects the stator vane to the adjusting ring outside of the housing of the turbo engine. The device further includes a projection on the end of the shank, and the projection projects past the rim of the opening when the stator vane is in an installed position.

Apparatus for adjusting stator vanes

Apparatus for the support and adjustment of stator blades of a gas turbine, in which an adjusting ring is connected to the stator blades by adjustment levers disposed outside the turbine housing. The adjusting ring is supported for rotation in the circumferential direction on a support ring, which has elastic resilience in the radial direction, the support ring being suspended on and centered in a movable manner on radial pins fixed in an outer housing of the turbine. The connection of the adjusting ring and the support ring is achieved by a ball-bearing which is pre-stressed. When the adjusting ring is displaced circumferentially, the stator blades are pivoted around suspension shafts by levers fixed to the shafts and connected to the adjusting ring for universal pivotal movement.

Apparatus for the adjustment of stator blades of a gas turbine

A valve for a fluid flow engine is constructed so that it can cause a required pressure build-up, so that it can drain excess fuel back to a tank, and so that the engine can be shut-off. Hot fuels that must be returned into the tank are prevented from damaging the fuel intake slots. The pressure build-up is controlled or determined by a separate fuel metering surface.

Growing community of inventors

Haimhausen, Germany

Georg Zotz