Mtu Aero Engines Ag

Harsimar Sahota

Alexander Halcoussis

Sergio Elorza Gomez

Georg Zotz

Vitalis Mairhanser

Giovanni Brignole

Manfred Lahmer

Ralf Homburg

A turbomachine () having a flow duct () with an annular inlet opening () and an annular outlet opening (), the inlet opening () and the outlet opening () being connected by an inner and an outer circumferential surface (), which radially bound the flow duct (), the flow duct () having a plurality of circumferentially distributed radially extending struts () whose leading edges () are spaced a distance (D) apart from trailing edges () of upstream guide vanes () and whose trailing edges () are spaced a distance (D) apart from leading edges () of downstream guide vanes ().

Turbomachine having a flow duct

A guide vane for arrangement in a gas duct of a turbomachine, including a guide vane blade and an outer platform which, relative to a longitudinal axis of the turbomachine, is arranged radially on an outside on the guide vane blade. The outer platform delimits the gas duct with an inner wall surface radially to the outside. The inner wall surface has a curved profile with an inflection point when viewed in an axial section, the inner wall surface having a concave curvature in a first axial section which is upstream from the inflection point with respect to a flow through the gas duct, and a convex curvature in a second axial section which is arranged downstream from the inflection point with respect to the flow through the gas duct.

Guide vane arrangement for a turbomachine, compressor module, and turbomachine

An intermediate duct () for disposition between an outlet of a low-pressure compressor and an inlet of a high-pressure compressor of a turbomachine, in particular of an aircraft engine is provided, the intermediate duct including an outer wall () and an inner wall () between which are disposed an optional exit stator ring () and at least one strut () extending radially with respect to a central axis of the intermediate duct (). The intermediate duct () is at least partially manufactured by additive manufacturing. A method for manufacturing such an intermediate duct (), and a turbomachine having such an intermediate duct () are also provided.

Additively manufactured intermediate duct for disposition between a low-pressure compressor and a high-pressure compressor, and corresponding manufacturing method

An engine, having a first, second, third and fourth quasi-stage, each with a stator and a downstream rotor, wherein a particular blade/vane solidity in the center section is in the first quasi-stage, at least 1.04 and at most 1.16 for the stator and at least 1.46 and at most 1.67 for the rotor; in the second quasi-stage, at least 1.13 and at most 1.32 for the stator and at least 1.32 and at most 1.61 for the rotor; in the third quasi-stage, at least 1.20 and at most 1.39 for the stator and at least 1.16 and at most 1.41 for the rotor; in the fourth quasi-stage, at least 1.37 and at most 1.63 for the stator and at least 1.15 and at most 1.41 for the rotor.

High pressure compressor for an engine

A turbomachine having at least one circulation structure is disclosed. The circulation structure has an annular space with baffle elements surrounding a main flow path and is open to the main flow path. A housing of the turbomachine to receive the circulation structure is divided in an axial plane into a front housing region and a rear housing region and the circulation structure is divided into a front structure region and a rear structure region in the axial plane of separation. A circulation structure divided into two parts in the axial direction and a method for the same is also disclosed.

Turbomachine, circulation structure and method

A gas turbine stage, in particular to an aircraft gas turbine. This gas turbine includes at least one casing having at least one bleed duct and at least one bore, and further includes at least one variable guide vane having a trunnion, a rotary plate, and a guide vane airfoil. The trunnion is disposed in the bore, and the guide vane airfoil is integrally formed with the rotary plate. The guide vane airfoil integrally formed with the rotary plate extends beyond this rotary plate in such a way that, viewed in the direction of flow of the gas path of the gas turbine, a flag corner of the guide vane airfoil, which corner faces the bleed duct and/or is in particular a virtual one, is located downstream of the beginning of the inlet opening of the bleed duct.

Growing community of inventors

Garching, Germany

Harsimar Sahota