Rolls-royce Deutschland Ltd & Co. Kg

Kay Heinze

Michael Ebel

Carsten Clemen

Ivo Szarvasy

Stefan Penz

Volker Herzog

Igor Sikorski

Manfred Baumgartner

The present invention relates to a method for producing an engine component having a cooling duct arrangement which has a plurality of cooling ducts, each having an inflow opening, the inflow openings being arranged according to a predefined pattern in an inflow surface of the engine component, and each cooling duct opening into a recess in a wall of the engine component, along which wall a cooling film is to be formed. According to the invention, the pattern is formed in at least one subregion of defined size of the inflow surface, from a plurality of identical isosceles triangles, which are defined by a minimum spacing (k) and by a mean diameter (a) of the inflow openings correlating to the minimum spacing (k). This procedure reduces the complexity of the design process.

Method for manufacturing an engine component with a cooling duct arrangement and engine component

A combustion chamber assembly group, and a mounting method therefor, includes a combustion chamber for an engine that includes a curved combustion chamber wall extending along two spatial directions, and a combustion chamber shingle affixed at an inner side of the combustion chamber wall and having a shingle edge defining the outer contour of the shingle. For an at least sectional abutment of the shingle edge at the combustion chamber wall with a minimum clamping force in an operational state of the engine, the shingle is mounted to the combustion chamber wall in a mounting state in which the shingle at least at one section of the shingle edge has a curvature with respect to at least one of the spatial directions that differs from the curvature of the combustion chamber wall with respect to this spatial direction.

Combustion chamber assembly with different curvatures for a combustion chamber wall and a combustion chamber shingle fixed thereto

A combustion chamber assembly for an engine with at least one tile component, on the cold side of which facing away from a combustion space, a positioning aid with at least two positioning elements, wherein a defined position relative to the combustion chamber component is predefined for the tile component via the contact of the at least two positioning elements on at least one contact face of the combustion chamber component in two spatial axes.

Combustion chamber assembly with shingle part and positioning facility

A combustion chamber shingle arrangement of a gas turbine, including a combustion chamber shingle, at least one threaded bolt configured for attaching the combustion chamber shingle, and a base body connecting the threaded bolt to the combustion chamber shingle, wherein the base body comprises a platform and a connection area that connects the platform to the combustion chamber shingle, wherein the threaded bolt is arranged at the platform, and wherein a hollow space is embodied between the platform and the combustion chamber shingle.

Combustion chamber shingle arrangement of a gas turbine

A plate-shaped structural component of a gas turbine with a base body that, at least in one edge area, is provided in one piece with a side bar that is embodied to ne substantially rectangular to the surface of the base body, wherein the base body has a different thickness than the side bar, wherein a supporting body, which is connected in one piece with the base body and the side bar and is provided with a substantially triangular cross section, is arranged between the side bar and the base body, being provided with multiple slit-like recesses.

Plate-shaped structural component of a gas turbine

A method for mounting a combustion chamber of a gas turbine engine, wherein an annular outer combustion chamber wall and an annular inner combustion chamber wall are brought in position with respect to one another and are connected to a head plate, and wherein subsequently a combustion chamber head is mounted, characterized in that the head plate is connected to the outer combustion chamber wall and the inner combustion chamber wall by means of rivets that are arranged in a circumferentially distributed manner, and that subsequently the combustion chamber head is brought in position and is screwed together by means of threaded bolts and nuts to the arrangement of head plate, outer combustion chamber wall and inner combustion chamber wall, which is pre-mounted by means of the rivet.

Method for mounting a combustion chamber of a gas turbine engine

A gas turbine combustion chamber with a combustion chamber wall and with at least one shingle that is fastened to the combustion chamber wall at a distance from the same, wherein the shingle has a shingle edge that abuts the combustion chamber wall, wherein the combustion chamber wall and the combustion chamber shingle respectively have at least one mixed air hole, and wherein a tubular fastening element provided with a ring flange is inserted through the mixed air hole of the combustion chamber wall, abutting the side of the combustion chamber wall that is facing away from the combustion chamber shingle with the ring flange, characterized in that, at its exterior side, the fastening element is provided with first snap-in means that are in mesh with second snap-in means that are formed at a tubular snap-in element that braces the combustion chamber shingle against the combustion chamber wall.

Growing community of inventors

Ludwigsfelde, Germany

Kay Heinze