Mtu Aero Engines Ag

Mtu Aero Engines Gmbh

Joerg Frischbier

Karl Maar

Hermann Klingels

Martin Pernleitner

Jens Wittmer

Hans-Peter Hackenberg

Rotor blade () to be arranged in a gas conduit () of a turbomachine (), having a rotor blade airfoil (), which radially inwardly has a chord length S, radially outwardly has a chord length S, and in a radial position rinbetween has a chord length S, the chord length Sin the radial position rbeing at least equal to the chord length Sradially inwardly (S<S), and the chord length Sradially outwardly corresponding at most 0.9 times the chord length Sin the radial position rinbetween (Sa<0.9 S).

Rotor blade for a turbomachine, associated turbine module, and use thereof

Described is a blade for a high-speed turbine stage of an aircraft gas turbine, in particular of an aircraft engine, the blade including a radially inner blade root, and an airfoil extending radially outwardly from the blade root. It is provided that the blade be shroudless and that the airfoil have a radially outer end portion that is positionable opposite a rub surface when the blade is in an installed state, and that the airfoil have a radially inner chord length that is at least 1.1 times, preferably at least 1.2 times, in particular at least 1.3 times a radially outer chord length, the inner chord length being measured at the airfoil directly above the blade root, and the outer chord length being measured at the airfoil in the region of or below the end portion.

Shroudless blade for a high-speed turbine stage

Described is a blade for a high-speed turbine stage of an aircraft gas turbine, in particular of an aircraft engine, the blade including a radially inner blade root, a radially outer shroud, and an airfoil extending between the blade root and the shroud. It is provided that the outer shroud have only a single sealing element, which projects radially from the shroud, in particular only a single sealing fin.

Blade for a high-speed turbine stage having a single sealing element

A blade row for a turbomachine, in particular a gas turbine, is disclosed. The blade row has a number of first blade arrangements each having at least one first blade and a first shroud with a first extension in the circumferential and/or axial direction and at least a number of additional blade arrangements each having at least one additional blade and one additional shroud with an additional extension in the same direction, which is different from the first extension.

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Dachau, Germany

Joerg Frischbier