Mtu Aero Engines Ag

Petra Kufner

Erwin Bayer

Walter Gieg

Rudolf Stanka

Thomas Hess

Karl Maar

Norman Cleesattel

Oliver Thiele

Joachim Lorenz

Carsten Schoenhoff

Jens Wittmer

Wolfgang Bickmeier

Rene Schneider

Marc Hassler

René Schneider

Markus Schlemmer

Thomas Heß

Sven-Jürgen Hiller

A gas turbine includes a housing and an outer sealing ring. In an assembled state of the housing and the outer sealing ring, a first planar structure of the outer sealing ring is axially moveable with respect to a second planar structure of the housing against a direction of flow through the gas turbine.

Gas turbine with axially moveable outer sealing ring with respect to housing against a direction of flow in an assembled state

The aircraft-engine gas turbine includes an outer sealing ring for sealing an array of rotor blades that can be attached to a housing by a clamping mechanism () in a friction fit, and a plurality of ring segments (), whereina free axial path length (a) of a sealing ring segment counter to the direction of through-flow is at least as large as an axial engagement (a) of a rotation locking member () of the outer sealing ring (a&#x2265;a), which is free of form fit counter to the direction of through-flow, and/or an axial overhang (a) of a radial mounting rail () of the outer sealing ring (a&#x2265;a), and/or an axial offset (a, a) of a sealing fin (); and/ora quotient of a specific clearance sum of the outer sealing ring attached to the housing in a friction fitand pi is at least as large as a difference between a maximum outer diameter of the outer sealing ring and a minimum inner diameter of the flow channel inlet of the housing.

Gas turbine

A containment for a continuous flow machine, in particular for a gas turbine, is disclosed. The containment has at least one annular housing with at least one axial section of lesser radial wall thickness and at least one axial section adjacent thereto of greater wall thickness, where the housing is designed and constructed so that the section of greater wall thickness is at a distance in the axial direction of the continuous flow machine from a trailing edge of a guide vane lying downstream in the direction of flow of the continuous flow machine, and extends downstream in the direction of flow of the continuous flow machine over a leading edge of the next downstream guide vane.

Containment for a continuous flow machine

The invention relates to a run-in coating () for an outer air seal of a turbomachine, especially of an aero engine, comprising a substrate () of segmented form which carries a honeycomb structure () with an run-in surface () to face rotor blades of a rotor of the turbomachine, wherein a radial thickness of the honeycomb structure () varies in the circumferential direction. The invention furthermore relates to an outer air seal for a turbomachine and also to a turbomachine with an outer air seal.

Run-in coating for an outer air seal of a turbomachine

A housing element () for an intermediate turbine housing of a gas turbine, in particular an aircraft gas turbine; the housing element () being installable or installed in the intermediate turbine housing radially outwardly, in each case between a plurality of circumferentially spaced struts; the housing element () having a planar form and, relative to the radial outer side () thereof, a plurality of depressions (), is provided. On the radial inner side () thereof, the housing element () has at least one recess () that is configured outside of the regions in which depressions () are formed on the radial outer side ().

Housing element for an intermediate turbine housing

The present invention relates to a turbomachine with a housing structure as well as a corresponding housing structure an outer housing wall and an inner housing wall, which, passing around the flow duct of the turbomachine at a distance from each other, surround the outer side of the flow duct, wherein the inner housing wall of the housing structure is formed by an OAS (outer air seal, outer fluid seal) in the region of the rotating blades of the turbomachine, which rotate around an axial axis of the turbomachine, wherein a heat protection shield is constructed between the outer housing wall and the OAS. The heat protection shield has a plurality of spacers in the peripheral direction that are distanced from one another in the peripheral direction and are situated additionally to and in the radial direction outside of the heat protection element.

Housing structure of a turbomachine with heat protection shield

A method for disassembly of a rotor, in particular the front rotor of a gas turbine with a housing and a channel which diverges in a direction of flow and in which the rotor is arranged, is disclosed. An embodiment of the method includes axially displacing an outer sealing ring that is radially opposite the rotor, and whose minimum inside diameter is smaller than the maximum outside diameter of the rotor, against the direction of flow. Then, the rotor is axially displaced against the direction of flow, in particular out of the housing. A method for assembly of such a rotor, as well as a tool for the same, is also disclosed.

Method for disassembly and assembly of a rotor of a gas turbine

A turbomachine includes a sealing segment ring that is provided between a front guide vane row and a back guide vane row for sealing a radial gap between a casing section and a rotor blade row rotating between the guide vane rows, wherein the sealing segment ring has a plurality of identical sealing segments and at least one of the guide vane rows has a plurality of identical guide vane segments, wherein the sealing segments each have a plurality of engagement sites lying adjacent to one another in the peripheral direction for interaction with securing elements of this guide vane row, wherein the engagement sites and securing elements are distributed uniformly over the periphery and the engagement sites are a multiple of the securing elements, a sealing element, and a guide vane segment.

Turbomachine, sealing segment, and guide vane segment

The aircraft-engine gas turbine includes an outer sealing ring for sealing an array of rotor blades that can be attached to a housing by a clamping mechanism () in a friction fit, and a plurality of ring segments (), wherein a free axial path length (a) of a sealing ring segment counter to the direction of through-flow is at least as large as an axial engagement (a) of a rotation locking member () of the outer sealing ring (a&#x2267;a), which is free of form fit counter to the direction of through-flow, and/or an axial overhang (a) of a radial mounting rail () of the outer sealing ring (a&#x2267;a), and/or an axial offset (a, a) of a sealing fin (); and/or a quotient of a specific clearance sum of the outer sealing ring attached to the housing in a friction fit.

A housing section of a turbine engine compressor stage or a turbine engine turbine stage that, in particular, has a closed and annular-shaped, radially outer casing. The radially outer casing has radially inwardly extending webs that are angled at a slant relative to the radius.

Housing section of a turbine engine compressor stage or turbine engine turbine stage

The present invention relates to a gas turbine having a housing (), an outer sealing ring () that can be fastened detachably to the housing, a clamping member () for clamping the outer sealing ring and the housing together radially, and a rotation locking member that has at least one housing groove () and a radial flange () of the outer sealing ring that can be locked against rotation in the housing groove in form-fitting manner with play (s) in the axial and/or peripheral direction.

Growing community of inventors

Poing, Germany

Petra Kufner