Mtu Aero Engines Ag

Mtu Aero Engines Gmbh

Franz Malzacher

Alexander Boeck

Markus Brettschneider

Martin Hoeger

Martin Pernleitner

Guenter Ramm

Karl Maar

Alexander Böck

Marc Nagel

Christoph Mueller-Schindewolffs

A guide vane ring and/or a rotor blade ring for a low-pressure turbine of an aircraft gas turbine of a turbofan engine includes a plurality of airfoils disposed consecutively in a direction of rotation. The plurality of airfoils includes a first airfoil and a second airfoil adjacent to the first airfoil in the direction of rotation. The first and second airfoils are disposed relative to each other such that a ratio e/t, viewed in a conical section, results from

Guide vane ring and rotor blade ring for a turbofan engine

The present invention relates to a rotor blade () for arrangement in a gas duct () of a turbomachine (), having a rotor blade airfoil (), which, viewed in a tangential section, has a blade airfoil profile () with a leading edge radius RVK and a rotor blade airfoil thickness d, wherein the blade airfoil profile () is thickened, at least in sections, specifically the blade airfoil thickness d is specified, in relation to the front edge radius RVK, such that (2d/Rvk2)−d≤5.5.

Rotor blade for a turbomachine

Disclosed is a turbomachine including a stator, a rotor rotatable about an axis of rotation, and an annulus for carrying a core flow, the annulus having a side wall on the stator and a side wall on the rotor, at least one airfoil array having a plurality of airfoils being disposed in the annulus. In a departure from an ideal aerodynamic annulus contour, a radial annulus enlargement begins upstream of the airfoils and extends downstream up to an aft portion of the airfoil array that follows the ideal aerodynamic annulus contour. Also disclosed is an airfoil for such a turbomachine.

Turbomachine having an annulus enlargment and airfoil

A housing for a gas turbine is disclosed. At least one wall element is housed on the housing so as to move, which limits a flow channel of the housing in the radial direction from a rotational axis of a rotor of the gas turbine toward the exterior. The housing includes at least one variably adjustable guide blade which extends through the wall element into the flow channel. The wall element can be moved between a sealing setting, in which the wall element makes contact at least in a partial area of a side of a blade leaf of the guide blade facing toward the wall element, and an open setting, in which the blade leaf and the wall element are spaced some distance apart from one another. A gas turbine as well as a process for operating a gas turbine is also disclosed.

Housing for a gas turbine, aircraft engine, and a process for operating a gas turbine

A guide blade for a gas turbine is disclosed. The guide blade includes a blade leaf having a receptacle in which at least one sealing element is arranged, where the sealing element is movable relative to the blade leaf between a sealing setting, in which the sealing element is at least partially moved out of the receptacle, and a storage setting, in which the sealing element is moved back into the receptacle. The guide blade further includes at least one fluid channel by which fluid under pressure can be routed into the receptacle in order to move the sealing element from the storage setting into the sealing setting. An inlet opening of the fluid channel is formed on a pressure-side surface of the blade leaf. A housing as well as a gas turbine having at least one guide blade is also disclosed.

Guide blade for a gas turbine

A turbo engine, particularly a gas turbine aircraft engine, has compressor components, turbine components, and at least one combustion chamber. At least one support rib is in flow channel between two turbine components, connected one behind the other. Each support rib diverts a flow through the flow channel. A preferably cylindrical guide element runs within each support rib. Each support rib has a suction side with a greater thickness toward a radially inner flow channel wall as well as toward a radially outer flow channel wall, when viewed in the radial direction. Each support rib has a pressure side with a greater thickness toward a radially inner flow channel wall as well as toward a radially outer flow channel wall, when viewed in the radial direction. The front edge and the rear edge of each support rib are inclined in the meridian direction.

Turbo engine

A flow structure of a gas turbine, in particular for an aircraft engine, in a transitional channel between two compressors or in a transitional channel between two turbines or in a transitional channel of a turbine outlet housing downstream from a low-pressure turbine is disclosed. Supporting ribs are positioned in the transitional channel and spaced a distance apart in the circumferential direction of the transitional channel. At least one guide vane and/or guide rib is positioned between two supporting ribs spaced a distance apart from one another. The flow outlet edge of the guide rib or each guide rib runs upstream from the flow outlet edges of the supporting ribs.

Growing community of inventors

Groebenzell, Germany

Franz Malzacher