Siemens Energy, Inc.

Siemens Energy Global Gmbh & Co. Kg

Johan Hsu

Andrew G McQuiggan

Jay Alan Morrison

Robert W Dawson

Robert H Bartley

Dustin C Boudin

Muzaffer Sutcu

James Michael Zborovsky

Wojciech Dyszkiewicz

Jordan Metz

A sealing assembly positioned between a first component having a first interface and a second component having a second interface is provided. The sealing assembly includes a flat bracket fixedly attached to the first interface to define an extension and a floating seal including a body portion, a first U-shaped channel arranged to engage the extension, and a second U-shaped channel inhibiting movement of the floating seal in an axial direction while allowing movement in a radial direction, and the second U-shaped channel allowing movement in the axial direction and inhibiting movement in the radial direction.

Seal assembly between a transition duct and a first stage vane structure

A cooled component wall () with a combustion gas () on one side () and a coolant gas () with higher pressure on the other side (). The wall includes a cooling chamber () with an impingement cooling zone (), a convective cooling zone (), and a film cooling zone (). Impingement holes () admit and direct jets () of coolant against the wall, then the coolant passes among heat transfer elements such as channels () and fins () to the film cooling zone () where it passes through holes in the wall that direct a film of the coolant along the combustion side of the wall. The chamber may be oriented with the impingement zone () downstream and the film cooling zone () upstream, relative to the combustion gas flow (). This provides two passes of the coolant () in opposite directions over the respective opposite sides of the wall ().

Cooling arrangement for a turbine component

A transition duct having an inlet opening and an outlet opening and a body portion extending between the inlet and outlet openings at respective inlet and outlet ends. The inlet opening defines a generally circular cross-section for the body portion and has a geometric center, and the outlet opening defines a generally rectangular arc-like cross-section. The body portion has an internal profile substantially in accordance with coordinate values X, Y and Z at an angle &#x3b8;, as set forth in Table 1, where each of the X, Y and Z coordinate values are taken at a sweep angle &#x3b8; passing through the section origin and measured from a first plane defined by the inlet end and increasing toward a second plane defined by the outlet end.

Transition duct for gas turbine engine

One embodiment of a transition-to-turbine seal () comprises a transition exit seal () adapted for fixed attachment to an exit rail () of a transition (), and a stage-1 seal (). The stage-1 seal () comprises an axial seal slot () comprising parallel walls () adapted to slidingly engage a first male member () of the transition exit seal (). The stage-1 seal () also comprises a radial seal slot () comprising parallel walls () adapted to slidingly engage a plate () of a row 1 vane segment (). The transition-to-turbine seal () thus provides both axial and radial freedom of movement. Materials and coatings for the transition exit seal () and the stage-1 seal () are selected to promote preferential wear of these components relative to wear of the surface of the row 1 vane segment (). Wear of the exit rail () is reduced or eliminated due to the noted fixed attachment.

Transition-to-turbine seal apparatus and kit for transition/turbine junction of a gas turbine engine

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Orlando, FL, United States of America

Johan Hsu