Mtu Aero Engines Ag

Mtu Aero Engines Gmbh

Rolls-royce Deutschland Ltd & Co. Kg

Alexander Boeck

Franz Malzacher

Sven Schmid

Manfred Feldmann

Inga Mahle

Lothar Albers

Norbert Huebner

Stephen Royston Williams

Robert Dietrich

The present invention relates to a blade for a gas turbine, in particular of an aircraft engine, which is produced at least in part from ceramic matrix composite with a plurality of superimposed fabric layers, wherein at least one pair of superimposed fabric layers comprises a first fabric layer that has at least one first point of interruption between two mutually facing first edges of this fabric layer, and a second fabric layer that has at least one second point of interruption adjacent to the first point of interruption between two mutually facing second edges of the second fabric layer, this second point being displaced from the first point of interruption.

Gas turbine blade

The invention relates to a positioning element for a guide vane arrangement of a guide vane stage of a gas turbine, with at least one base section curved in the peripheral direction; a plurality of uptake openings arranged next to each other in the peripheral direction on the base section, whose aperture axis runs substantially in the radial direction and which are designed to take up a respective radially inner guide vane section; a coupling section provided on the base section, which is or can be coupled to a seal carrier of a seal arrangement. According to the invention, it is proposed that at least one recess is provided in the base section, which is arranged between two neighboring uptake openings and runs from inside to outside at least in the radial direction.

Positioning element with recesses for a guide vane arrangement

A turbine center frame for a gas turbine having a plurality of first components and a plurality of second components alternately mutually adjacently disposed in circumferential direction and bounding a hot gas-conducting flow channel in radial direction, the first components each having two first overlapping portions, and the second components each having two second overlapping portions. In a transition from a first component to a second component, one of the first overlapping portions and one of the second overlapping portions overlap. A centering element, against which, the first components and the second components are braced along the circumferential direction and in the radial direction, centers the first components and the second components relative to a central axis of the turbine center frame. The first components and the second components are manufactured of a ceramic matrix composite, and each first component and each second component are provided with a first supporting portion and a second supporting portion mutually spaced apart at a distance in the circumferential direction, the first supporting portion and the second supporting portion being configured to act from different sides upon the centering element in the radial direction.

Turbine center frame having a centering element

The invention relates to a turbine center frame for an aircraft gas turbine, with a plurality of first components and a plurality of second components, which, in the peripheral direction, are arranged alternately next to one another and, in a radial direction, bound a flow duct conveying hot gas, wherein the first components each have two first overlapping segments and the second components each have two second overlapping segments with a respective region of the transitioning from a first component to a second component or vice versa, a first overlapping segment and a second overlapping segment are arranged overlapping, and with at least one centering element, at which the first components and the second components are supported along the peripheral direction and in a radial direction with the first components and the second components essentially centered with respect to a central axis of the turbine center frame.

Turbine center frame with centering element and spacer element

A sealing assembly for a gas turbine is provided, especially an aircraft gas turbine, including: a first component having a first flange portion and a second component having a second flange portion; in the area of the first flange portion and the second flange portion, the first component and the second component being detachably intercoupled by a bolt connection; between the first component, especially a rounded portion, and the second component, especially the second flange portion, a variable interspace being provided that is at least partially sealed by at least one sealing element. The sealing element has a first sealing portion that rests against the first component, especially against the rounded portion, and a second sealing portion that rests against the second component, especially against the second flange portion; the first sealing portion and the second sealing portion being interconnected and extending obliquely relative to each other.

Sealing assembly for a gas turbine

A seal arrangement comprising a first and second components made of a ceramic fiber composite material and comprising first and second bounding sections with first and second overlapping sections and first and second securing sections which are connected to and projects from the first and second bounding sections. The first and second overlapping sections are arranged at least partially overlapping such that the first and second bounding sections form an essentially continuous bounding surface. A separation between the first and second securing sections is at least partially sealed by a seal element which comprises at least one first sheet-metal element arranged along the first securing section and at least partially bridging the separation between the first and second securing sections.

Seal arrangement for a gas turbine

A seal system for a turbomachine, in particular a gas turbine, which includes a first component (A,B), a second component (), a flap () for sealing a gap between the first and second components, and a leaf spring, which includes a first leg () and a second leg (), in a mounting state in which the flap and the second component do not contact each other, a projection of an abutment area () of the first component (A,B), against which the first leg () is supported via the flap (), is situated perpendicularly to a contact line (K) through at least two contact points of the first leg () with the flap (), at least partially within a bearing surface (A) of the first component (A,B), against which the second leg () of the pretensioned leaf spring is supported.

Turbomachine seal system

The invention relates to a guide means () for a gas turbine, in particular for an aircraft engine, having at least one casing element (); having at least one first duct segment (), which is arranged in the radial direction on the inside of the casing element (), by means of which at least one duct (), through which gas can flow, is at least partially delimited outward in the radial direction; having at least one second duct segment (), which is arranged in the radial direction on the inside of the first duct segment (), by means of which the duct () is at least partially delimited inward in the radial direction; and having at least one guide vane ().

Guide means for a gas turbine and gas turbine having such a guide means

A coupling assembly, including a first component and a second component overlapping in a join region; a joining device allowing the first and second components to rest against each other clampingly and region; the joining device including a clamp resting on the first component and the second component and having a bolt connection adapted for securing the clamp to the first and second component. The first and second components are manufactured from a ceramic matrix composite; the first component having a holding portion including a front side facing the clamp, a rear side facing away from the clamp, and a receiving opening; and the bolt connection having a bolt portion that extends through the receiving opening and, at the end thereof facing away from the clamp, having a bracing portion angled relative to the longitudinal axis of the bolt portion and that rests against the rear side.

Coupling assembly for components of ceramic matrix composites for a turbine center frame

A turbine blade () having an airfoil (). In its radially outer region, the turbine blade () has at least one shroud () or at least one shroud segment, as well as at least one cutting tooth () which is intended to engage at least once into portions of a turbine casing during use of the turbine blade (). The cutting tooth () is connected to the shroud () or the shroud segment.

Turbine blade having a shroud and a cutting tooth

A sealing system including a first component at least partially manufactured from ceramic fiber composite materials, a second component at least partially manufactured from ceramic fiber composite materials, and a sealing element accommodated between the first component and the second component. The sealing element is designed as a sealing strip. It is provided that at least one recess accommodating the sealing element is formed on the first component and/or on the second component, the recess having a cross-sectional profile including an inner section which is concave toward the sealing element, the radius of curvature of the inner section being selected in such a way that it may be formed with the aid of continuous, curved fibers of the ceramic fiber composite material, the fibers being oriented in such a way that they lie essentially in parallel to the cross-sectional plane of the cross-sectional profile.

Sealing system made of ceramic fiber composite materials

A guide vane () for a turbomachine, having a sealing device (') at the radially inner end region of the guide vane () for sealing leakage flows () between the guide vane () and an inner ring () joined thereto. The sealing device (&#x2032;) is movably configured relative to the guide vane (). The sealing device (&#x2032;) is positionable in at least one open or in a closed configuration for sealing the leakage flows (). Also, a guide vane (), as well as a turbomachine.

Guide vane for a turbomachine having a sealing device; stator, as well as turbomachine

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 roller bearing, particularly a needle bearing, for arranging on a pivot pin of a variable guide vane of a turbomachine, is disclosed. The roller bearing includes at least one radially elastic needle which has two opposing end regions and at least one roller region arranged between the end regions and constructed in a cross-sectionally thickened manner. The end regions roll off at associated raceways of a bearing housing of the roller bearing and the roller region is arranged in the region of an associated groove of the bearing housing. A variable guide vane with at least one such roller bearing, a housing of a turbomachine with such a guide vane, as well as a turbomachine, is also disclosed.

Roller bearings, in particular needle bearings, for arranging on a pivot pin of a variable guide vane of a turbomachine

A guide mechanism for a gas turbine has a casing supporting on its interior a duct delimited by radially inner and outer duct segments. A variable guide vane located at least partially within the duct can rotate about an axis of rotation to guide flow of a fluid in the duct. The radially inner duct segment is fastened to the guide vane and is retained on the casing element via the guide vane, which is mounted on the casing element via a bushing inserted in the radial direction from outside to inside into a passage opening of the casing element.

Growing community of inventors

Kottgeisering, Germany

Alexander Boeck