Rolls-royce Deutschland Ltd & Co. Kg

Technische Unversität Berlin

Marcel Schmidt

Matthias Driess

Reinhard Schomäcker

Reinhard Schomaecker

Alexander Krentz

Burgert Blom

Systems and methods for reducing heat exposure of a turbine casing in a gas turbine engine may be provided. The system may include a blade track coupled with a turbine casing with a clip. The system may further include a nozzle guide vane coupled to the turbine casing. A cavity may be formed by an end of the blade track, the clip, and a portion of the nozzle guide vane. A heat shield may be positioned between the clip and the end of the blade track in the cavity such that an edge of the heat shield and the portion of the nozzle guide vane form a gap. The heat shield and the nozzle guide vane may be positioned such that the gap closes in response to the heat shield and the nozzle guide vane thermally expanding.

Turbine casing heat shield in a gas turbine engine

A catalyst for the hydroformylation of at least one olefin, having a ligand fo the general formula (1) &#x2014;R, R, Rselected from the group including substituted and non-substituted alkyl, substituted and non-substituted aryl, substituted and non-substituted alkenyl, substituted and non-substituted alkinyl, substituted and non-substituted cycloalkyl, and substituted and non-substituted heterocycles, wherein R, Rand Rcan each be the same or different, L is selected from a group having a sandwich complex, an oxygen group, substituted and non-substituted alkylene or heterocycles, and substituted aryl or heteroaryl; and aryl and heteroaryl is each substituted with groups which contain at least two heteroatoms and are coupled to the Si via the at least two heteroatoms of the substituents, &#x2014;n=1-10, preferably 1-5, particularly preferably 1, 2, or 3; and the ligand is coupled to the metal M from the group VIIIb of the periodic table of elements via the Si group.

Catalyst for the hydroformylation of olefins, and use thereof

A subassembly of a gas turbine engine includes a heat shield and carrier subassembly for a turbine section are disclosed. The carrier includes support features to couple to an engine casing. The upstream end of the carrier includes a radially inward arm extending toward to an engine axis. The outer end of the radially floating heat shield is coupled to the radially inward arm via a pin-and-slot joint configured to allow movement of the heat shield relative to the radially inward arm of the carrier. In response to thermal expansion and contraction of the vane, the heat shield is configured to move radially outward and inward, respectively, relative to the radially inward arm to maintain contact with the outer platform of the vane.

Heat shield for a gas turbine engine

A transport securing device of an aircraft gas turbine includes a securing element, which at its two end areas is each provided with a first and a second connecting element, with the first connecting element being designed to be suitable for fastening to a front suspension device and the second connecting element being designed to be suitable for fastening to a rear suspension device of an aircraft gas turbine.

Growing community of inventors

Berlin, Germany

Marcel Schmidt