Mtu Aero Engines Ag

Mtu Aero Engines Gmbh

United Technologies Corporation

Other

Mtu Motoren-und Turbinen-union Munchen Gmbh

Mtu Motoren-und Turbinen-union Muenchen, Gmbh

Werner Humhauser

Hermann Klingels

Georg Zotz

Karl-Hermann Richter

Rudolf Stanka

Nicholas R Leslie

Fadi S Maalouf

Erich Steinhardt

Ulrich Knott

Vitalis Mairhanser

Roland Matzgeller

Josef Reischl

Klaus Breitschwerdt

Hans Juergen Schmuhl

Karlheinz Manier

Siegfried Boettcher

Manfred Feldmann

Thomas Uihlein

Sergio Elorza Gomez

Lothar Albers

Norbert Huebner

Hans-Peter Hackenberg

Karl Maar

Stefan Hagen Weber

Jochen Gier

Alexander Kloetzer

Alois Eichinger

Moritz Wirth

Manfred A Daeubler

Carsten Butz

Stephen Royston Williams

Patrick Wackers

David Koch

Ulrike Hain

Herman Klingels

Renate Mendritzki, Legal Representative

Horst Mueller-Wittek, Legal Representative

Walter Waschka

Peter Klaus Rued

Claus Riegler

Eckart Heinrich

Klaus Peter Rued

Josef Wagner

Hugh Alun John Jackson

Manfred A Däubler

The invention relates to an axially divided inner ring as well as a variable vane cascade for an aircraft engine. The inner ring and the vane cascade improve the efficiency of the aircraft engine in that differently formed vanes and/or vane mounts are formed respectively in the inner ring or in the vane cascade.

Inner ring segment, axially divided inner ring and variable vane cascade for an aircraft engine

The invention relates to a compressor for an engine, wherein the compressor has compressor stages arranged in succession in a flow direction of the compressor and each compressor stage has a rotating blade cascade and a guide vane cascade arranged downstream of the rotating blade cascade and the rotating blade cascade and the guide vane cascade each have an aspect ratio.

Compressor for an engine

Described is a connecting device () for a variable vane () of a gas turbine (), in particular of an aircraft gas turbine, the connecting device including a trunnion element () connected to a respective vane (); a lever element () connected to the trunnion element (), the lever element () and the trunnion element () being movable together about a trunnion axis of rotation (ZD). It is provided that the lever element () and the trunnion element () be aligned with each other by a positioning element (), the positioning element () being received in a trunnion receptacle () and a lever receptacle ().

Connecting device for a variable vane of a gas turbine

Disclosed is a lever linkage for the rotationally fixed connection of a guide vane to a lever of a guide vane adjusting device of a turbomachine, wherein the guide vane has a vane shaft, which extends along a vertical axis. In accordance with the invention, the lever is formed in one piece at a radially outer end of an essentially hollow cylindrical clamping sleeve, which coaxially surrounds the vane shaft in sections, and the vane shaft and the clamping sleeve are coupled by way of a longitudinal side form-fitting connection or a front-end form-fitting connection, and the vane shaft can be tensioned with the clamping sleeve along the vertical axis by means of a fastening element, in particular a threaded nut. In consequence thereof, a separation of two different force flows that act on the guide vanes is obtained, as a result of which local load peaks are reduced.

Guide vane connection

Disclosed is a lever connection for a guide vane adjustment for connecting a guide vane of a turbomachine to an adjusting ring of an actuator, which is arranged in such a way that an adjusting lever of the lever connection is pushed radially from a first mounting direction, in relation to a machine longitudinal axis of the turbomachine, onto a vane shaft of the guide vane, and is locked with the vane shaft in a form-fitting and, in particular, rotationally rigid manner by a movement in a second mounting direction; a mounting method; and a turbomachine.

Lever connection of a guide vane adjustment for turbomachinery

The present invention relates to a housing for a gas turbine compressor, having an operating duct for taking up several rows of rotating blades arranged one behind the other axially, wherein a wall of the operating duct has a first air bleed, wherein the housing has a cooling passage for cooling said operating duct wall by conveying air from the first air bleed to a first outlet passage for supplying at least one first bleed air consumer, wherein the first outlet passage is arranged downstream of the first air bleed, and wherein the operating duct wall has a second air bleed downstream of the first air bleed, and the housing has a discharge passage from said second air bleed to a second outlet passage for supplying at least one bleed air consumer.

Housing for a gas turbine compressor

The invention is directed to a guide vane ring for a turbomachine, in which a vane bearing is produced in the inner ring via platform plates of the vanes and reliability against disintegration is produced via journals that extend radially inward from the platform plates, as well as a turbomachine.

Guide vane ring and turbomachine

The invention relates to a module for a gas turbine comprising a rotationally symmetrical outer casing of a first material having a first linear thermal expansion coefficient, a rotationally symmetrical component for guiding hot gas of a second material having a linear thermal expansion coefficient which is lower than the first coefficient, at least one annular structure arranged radially within the component, and at least three struts having a radially inner end secured on the outer casing and a radially outer end secured on the annular structure. The component also comprises at least one first fixing which is free in radial direction and fixed in axial direction and arranged between the component and the outer casing and/or the annular structure, as well as at least three second fixings having an elastic effect in radial, axial and/or circumferential direction and being arranged between the component and the strut and/or the annular structure.

Module for a gas turbine

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 guide vane assembly according to the invention comprises an inner ring, on whose radially outer surface an uptake channel runs in the peripheral direction; a plurality of bearing members, which are arranged in the uptake channel of the inner ring; a plurality of guide vanes, each of which is inserted by its radially inner end into one of the bearing members; and at least one sealing element for sealing at least one gap between the inner ring and at least one of the bearing members and/or between two bearing members. A turbomachine according to the invention comprises a guide vane assembly according to the invention. A method according to the invention serves for the installation of a guide vane assembly.

Seal on the inner ring of a guide vane

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

An adjustable guide vane ring of a turbomachine having an inner ring, the guide vanes of which each have a radially inner vane disk with disk thickness increasing in the direction of flow and acting as a bearing pin; a guide vane, as well as an inner ring for such a guide vane ring, as well as a turbomachine are disclosed.

Guide vane ring, guide vane, inner ring and turbomachine

A locking element for a row of blades of a turbomachine includes a number of blades that are inserted by their roots in an anchoring groove on the rotor side and are thereby held in the radial direction in form-fitting manner in the anchoring groove. The locking element has a basic body that has a front bearing surface and a back bearing surface for form-fitting with opposite-lying groove surfaces, a front lock projection and a back lock projection for engaging in opposite-lying recesses of the anchoring groove, and a threaded region for interacting with a tightening element. Access to the threaded region for the tightening element is blocked on one side.

Locking element and turbomachine

An axially split inner ring for a fluid flow machine is disclosed. The inner ring is constructed for connecting to guide vanes and includes at least a first ring segment arranged upstream and a second ring segment arranged downstream. The second ring segment has a first sealing segment, where at least one section of the second ring segment is arranged in a radially inward manner relative to the first ring segment. A guide vane ring of a fluid flow machine and an aircraft engine are also disclosed.

Axially split inner ring for a fluid flow machine, guide vane ring, and aircraft engine

The present invention relates to a compressor stage for a gas turbine, in particular, an aircraft engine, having a row of rotating blades () and a row of guide vanes (), which is adjacent downstream, wherein the choke point &#x3c3; and the aspect ratio AR, which is defined by the quotient between average channel height (h) and average chord length (l), satisfy the condition&#x3c3;&#x3e;&#x2212;1.33&#xb7;AR+5.16.

Gas turbine compressor stage

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Moosburg, Germany

Werner Humhauser