Siemens Aktiengesellschaft

Paul Jenkinson

Paul Mathew Walker

Paul Padley

Mike McKenna

Steve Hannam

Jed Fentem

A method for assembling a stator stage of a gas turbine engine and an adjustment pin to perform the assembly method to lock a vane segment in a central section of the stator stage. The method includes inserting an adjustment pin into a through hole wherein the adjustment pin includes two end sections, inserting at least one wall segment of the vane segment into a slot of a central section, rotating the adjustment pin so that the central section is correctly positioned in the stator stage, deforming a deformable part of the adjustment pin so that the now deformed part establishes a force fit with at least one segment of a corresponding structure of the central section and thereby locking the adjustment pin and thus the central section in a fixed position in the stator stage.

Method for assembling a stator stage of a gas turbine engine

A laminated sheet for a gas turbine component, the laminated sheet has a first cover layer, a second cover layer and a first intermediate layer, wherein the first cover layer, the second cover layer and the first intermediate layer are stacked together on top of each other. The first intermediate layer is located between the first cover layer and the second cover layer. The first intermediate layer has at least one first elongated through hole, wherein a cooling fluid is flowable through the first elongated through hole.

Cooled composite sheets for a gas turbine

A vane device for a gas turbine is provided. The vane device includes a first airfoil having a first suction side and a first pressure side, a second airfoil having a second suction side and a second pressure side, an inner shroud and an outer shroud. The first airfoil and the second airfoil are arranged between the inner shroud and the outer shroud, wherein the first airfoil and the second airfoil are at least partially coated with a MCrAlY coating. At least the first suction side has a first coated surface section which is coated with a thermal barrier coating and which represents at least a part of the total surface of the first suction side. At least the inner shroud or the outer shroud has a further coated surface section which is coated with a further thermal barrier coating. A corresponding method of manufacturing is also provided.

Growing community of inventors

Lincoln, United Kingdom

Paul Jenkinson