Mtu Aero Engines Ag

Rtx Corporation

Norman Cleesattel

Rudolf Stanka

Martin Pernleitner

Manfred Dopfer

Marcus Woehler

Markus Schlemmer

Inga Mahle

Petra Kufner

Norbert Huebner

Patrick D Couture

Walter Gieg

Bernd Kislinger

Klaus Wittig

Manuel Hein

Manfred Schill

Christoph Lauer

Oliver Thiele

Joachim Lorenz

Carsten Schoenhoff

Gottfried Schuetz

Gottfried Schütz

Christoph Bichlmaier

Wilfrid Schuette

René Schneider

Carsten Schönhoff

Wilfried Schütte

Marcus Wöhler

Norbert Hübner

Inga Dr Mahle

According to an aspect, a gas turbine engine includes a turbine section with a turbine case and a plurality of turbine blades within the turbine case. The gas turbine engine also includes an active clearance control system with an active clearance control cooling air supply, a valve pneumatically coupled to the active clearance control cooling air supply, and a controller. The controller is configured to determine an active cooling control schedule adjustment based on a condition of the gas turbine engine, operate the active clearance control system according to an active cooling control schedule as modified by the active cooling control schedule adjustment, apply a decay function to the active cooling control schedule adjustment to reduce an effect on the active cooling control schedule adjustment, and resume operating the active clearance control system according to the active cooling control schedule based on an active cooling control condition being met.

Warm start control of an active clearance control for a gas turbine engine

A rotor blade for a gas turbine, in particular an aircraft gas turbine, having a blade root element and a stream deflection portion adjoining the blade root element () in the longitudinal direction of the blade (RR); respective centroids () of blade cross-sectional areas of the stream deflection portion residing on a common stacking axis (). It is provided that, starting from a first centroid () of a first blade cross-sectional area adjoining the blade root element (), the stacking axis () extend within a cone () whose apex resides within the first centroid (), and whose cone height (KH) extends orthogonally to the plane of the blade cross-sectional area; the angle (&#x3b2;) of the cone () being greater than 0&#xb0; and smaller than or equal to 4&#xb0;; preferably greater than or equal to 0.5&#xb0; and smaller than or equal to 2&#xb0;.

Stacking of rotor blades on centroids

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

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 gas turbine stage including a rotor blade array having a plurality of rotor blades and an adjacent stator vane array having a plurality of stator vanes which have leading edges facing the rotor blade array. In a first radial position of a rear face of the rotor blade array, a minimum axial gap is formed between this rear face and an opposite first contact region a stator vane leading edges, and in a second radial position of the rear face different from the first position, the minimum axial gap is formed between the rear face and an opposite second contact region. Between the first and second contact regions, this stator vane leading edge has an axial offset of no more than 0.6% of a radial height of the stator vane leading edge.

Gas turbine stage

Growing community of inventors

Zorneding, Germany

Norman Cleesattel