Mtu Aero Engines Ag

Mtu Aero Engines Gmbh

Mtu Aero Engine Ag

Bernd Kislinger

Markus Schlemmer

Manuel Hein

Oliver Thiele

Manfred Feldmann

Rudolf Stanka

Markus Brettschneider

Detlef Korte

Martin Pernleitner

Manfred Dopfer

Norbert Huebner

Klaus Wittig

Christoph Lauer

Wilfried Schuette

Manfred Schill

Joachim Wulf

Klaus Pirker

Marcus Woehler

Norman Cleesattel

Lukasz Sosnowka

Gerhard Brueckner

Bjoern Grueber

Marcin Regulski

Wilfried Schütte

Marcus Wöhler

Norbert Hübner

Gerhard Brückner

A stator vane for a turbomachine, including an airfoil having a leading edge and a trailing edge, which are interconnected by a suction side and a pressure side, the airfoil extending substantially in a radial direction between an inner platform and an outer platform, wherein, when viewed in an axial direction of the turbomachine toward the trailing edge, the trailing edge extends so as to be inclined at a first angle to the pressure side radially on an outside in relation to the radial direction at a circumferential position at which the trailing edge meets the outer platform, and wherein the first angle between the trailing edge and a tangent to the outer platform at a transition from the outer platform to the trailing edge is between 72° and 84°.

Stator vane for a turbomachine

A stator vane segment for a turbomachine is provided, in particular for a gas turbine, in particular for a turbine stage of a gas turbine. The stator vane segment has at least one stator vane and at least one shroud, in particular an outer shroud, having at least one first profile disposed on the shroud and adapted for attachment of the stator vane segment to the turbomachine casing, the profile extending in the circumferential direction at least partially over a circumferential length of the stator vane segment along the shroud of the stator vane segment and having at least one functional surface which extends at least partially in the axial direction and in the circumferential direction, at least one functional surface of at least one profile having at least two different curvatures in the circumferential direction in at least one radial plane perpendicular to an axis of rotation of the turbomachine in at least one temperature range below a defined operating temperature of the turbomachine.

Stator vane segment for a turbomachine

A guide vane airfoil for placement in a flow path portion of a turbomachine is provided, which, relative to a flow pattern in flow path portion, has a leading edge and, downstream thereof, a trailing edge, as well as a suction side and a pressure side; relative to a longitudinal axis of the turbomachine, viewed in the axial direction, in a radially inner portion, forming a first angle &#x3b1; with a circular arc about the longitudinal axis, and, in a radially outer portion, a second angle &#x3b3; with a circular arc about the longitudinal axis. The guide vane airfoil is inclined in the outer portion, thus &#x3b3;&#x2212;90&#xb0;, in terms of absolute value, being &#x3e;0&#xb0; (|&#x3b3;&#x2212;90&#xb0;|&#x3e;0&#xb0;), and the guide vane airfoil being more highly inclined in the outer portion than in the inner portion, thus &#x3b3;&#x2212;90&#xb0;, in terms of absolute value, being &#x3e;&#x3b1;&#x2212;90&#xb0; (|&#x3b3;&#x2212;90&#xb0;|&#x3e;&#x3b1;&#x2212;90&#xb0;).

Guide vane airfoil for the hot gas flow path of a turbomachine

The invention relates to a seal arrangement for a turbomachine, especially for an aircraft engine, for sealing a radial gap between a rotor and a stator, comprising at least one seal carrier for the supporting and/or fastening of at least one seal element, wherein the seal carrier comprises a radial crosspiece extending in a radial direction of extension and an axial crosspiece, formed as a single piece with the latter and extending in an axial direction of extension, wherein the seal element is arranged at a radially inner-lying bearing surface of the axial crosspiece, and a front ring or a front ring segment, viewed in the flow direction, and/or a rear ring or a rear ring segment, each with a radially running crosspiece.

Seal arrangement for a turbomachine, method for manufacturing a seal arrangement and turbomachine

A guide vane segmentfor a turbomachine includes a radially inner shroud platehaving a shroud plate surfacethat is adapted to be configured in the turbomachine to face a rotor bladeadjacent to the guide vane segment, and thereby essentially extend along an outer conical surface Kwhose cone axis coincides with the axis of rotation A of a rotor shaft. In a radially inner region, a rotor bladefor a turbomachine has a base platehaving a base plate surfacethat is adapted to be configured in the turbomachine to face a shroud of a guide vane rowadjacent to the rotor blade and thereby essentially extend along an outer conical surface Kwhose cone axis coincides with the axis of rotation A of a rotor shaft

Run-up surface for the guide-vane shroud plate and the rotor-blade base plate

A guide vane element for a gas turbine, the guide vane element having a first guide vane, a second guide vane distanced by one division in the peripheral direction, and at least one band joining these guide vanes, in particular, a radially inner band and/or a radially outer band, wherein at least one band joining these guide vanes has a vane-side surface having a contouring and a first front side in the peripheral direction having a groove, which is particularly straight in the axial direction, for the uptake of a sealing element.

Gas turbine guide vane element

The invention relates to a guide vane segment for an aircraft gas turbine, comprising at least a radially outer shroud and a radially inner shroud, which extend along a respective circular arc and together form a ring segment, wherein, in the radial direction, between the outer shroud and the inner shroud, a plurality of guide vanes are arranged next to one another in the peripheral direction (UR), the vanes being materially joined with the inner shroud and the outer shroud, in particular joined in one piece. At least two securing ribs are arranged next to one another are formed on the trailing end face for at least one guide vane, wherein an intermediate space delimited by the two securing ribs in the peripheral direction (UR) is formed, this space tapering from radially outside to radially inside.

Vane segment with peripheral securing

The invention relates to a guide vane segment for a gas turbine comprising at least one radially outer shroud and one radially inner shroud, which extend along a respective arc and together form an annular segment, wherein, in the radial direction between the outer shroud and the inner shroud, a plurality of guide vanes are arranged adjacent to one another in the peripheral direction and are joined to the inner shroud and to the outer shroud in a material-bonded manner and, in particular, are joined in a one-piece manner, wherein, in an axial lengthwise direction, the outer shroud comprises an axially front end wall element and an axially rear end wall element in such a way that the outer shroud and the two end walls form a tub-like profile in lengthwise section.

Guide vane segment with radical securing elements

A turbomachine has a stator and a rotor, wherein the rotor has blades () and the stator has a housing () and stationary guide vanes (), wherein the guide vanes () form guide vane rings () that adjoin the housing () with radially outwardly positioned ends () and adjoin the rotor with radially inwardly positioned ends. The guide vane rings are spoke-centered with the aid of bearing journals or guide pins () allocated to the housing () and penetrating through the housing (). The guide pins () extend at a slant relative to the radial direction and the axial direction of the turbomachine, wherein the ends () of the guide pins () reaching into the housing engage in forked elements () allocated to the radially outer ends () of the guide vane rings ().

Turbomachine, especially a gas turbine

Growing community of inventors

Reisgang, Germany

Bernd Kislinger