Siemens Energy, Inc.

Siemens Westinghouse Power Corporation

Hubertus Edward Paprotna

David Allen Little

Oran Bertsch

Richard Colin Charron

Kevin Michael Light

David B Allen

Jody W Wilson

Scott Thorsten Cloyd

Joshua D Kovac

Michael J Morrision

Brian Joseph Bohinsky

A combustion turbine includes a compressor section, a combustion section downstream from the compressor section, and a turbine section downstream from the combustion section. A diffuser section is downstream from the turbine section and has an outer wall, an inner wall, and at least one strut member extending therebetween. The outer wall has at least one first gas passageway therein, the inner wall has at least one second gas passageway therein, and the at least one strut member has at least one third gas passageway therein. The at least one first, second and third gas passageways deliver gas therethrough to assist attachment of a boundary layer to adjacent surfaces of the outer wall, the inner wall, and the at least one strut, respectively.

Combustion turbine including a diffuser section with cooling fluid passageways and associated methods

A cover assembly disposed about a rotor in a gas turbine engine. The cover assembly comprises a first cover, a second cover, and securing structure. The first cover is disposed about the rotor and comprises a forward end and an opposed aft end. The first cover is associated with a case mounting structure that is fixed to an engine casing. The second cover is disposed about the rotor and comprises a forward end and an opposed aft end. At least a portion of the first cover is disposed radially outwardly from the second cover. The securing structure couples the first cover to the second cover and permits relative radial movement between the first and second covers.

Cover assembly for gas turbine engine rotor

A seal assembly () for a gas turbine engine (). The seal assembly () includes a first seal member () including an abradable structure having at least first and second seal portions () radially spaced from each other, and a second seal member () including first and second seal surfaces () located in facing relationship to the first and second seal portions (), respectively. The first seal member () is formed of a honeycomb structure, and the first seal portion () of the first seal member () is a thin fin-like structure having a width in the axial direction of the turbine engine () that is less than the width of the second seal portion () in the axial direction.

Abradable labyrinth tooth seal

A blade gap control system configured to move a blade ring of a turbine engine relative to a blade assembly to reduce the gaps between the tips of the blades and the blade rings to increase the efficiency of the turbine engine is provided. The blade rings can be at an acute angle with respect to the rotational axis of the blade assembly. The axial movement of the blade ring can be done by a pressure differential supplied across the blade ring, the thermal expansion and/or contraction of a linkage or by a piston.

Blade clearance system for a turbine engine

Aspects of the invention are directed to a system for improving engine performance by reducing vane tip clearances in the compressor section of a turbine engine. According to aspects of the invention, an abrasive material can be attached to a rotor disc. Thus, if a vane tip contacts the rotor disc during engine operation, the vane tip is worn away by the abrasive material. The system can reduce the risk of substantial component damage resulting from a vane tip rubbing event. The abrasive material can be provided in the form of an insert that can be removably attached to the rotor disc. Thus, the insert can be readily removed and replaced when necessary.

Rotor disc assembly with abrasive insert

A seal usable between two thermally movable components to prevent fluids from mixing. For instance, the seal may be used to seal thermally movable components of a turbine engine that may include, but are not limited to, leading edge shrouds, isolation rings, ring segments, and vane segments. The seal may be formed from a body having a cross-section generally orthogonal to a longitudinal axis and include a first side, a second side generally opposite to the first side, a first end, and a second end generally opposite to the first end. A compliant material may be coupled to the first or second end, or both, and may absorb thermal expansion of the two thermally movable components. The seal may reduce leakage flow paths between the seal and the thermally movable components.

Seal usable between thermally movable components

A seal assembly and a rotary machine in combination with the seal assembly are provided. The seal assembly includes a seal and a biasing device configured to produce a force for mechanically biasing the seal toward a first position relative to the rotatable portion. The seal is further responsive to pressurized fluid for creating a force opposed to the biasing force to cause movement of the seal toward a second position closer to the rotatable portion than the first position, thereby reducing flow leakage between the stationary portion and the rotatable portion. The pressurized fluid may be the working fluid produced by or used within the rotary machine.

Seal assembly for a rotary machine

A biased, wear resistant seal assembly for sealing gas flow paths in a turbine system includes a planar shim having transverse legs at each end, a flattened leaf spring to urge the shim into sealing contact with the sealing surfaces of the turbine parts, and a shim protection material to avoid wear to the shim on the contact side. The shim protection material can include one or more metal fiber cloth layers secured to the shim, for example, by seam welding to a pair of rails or to the legs of the shim.

Biased wear resistant turbine seal assembly

A gas turbine system in which substantially all of the compressed air from the compressor portion of the gas turbine is used to fluidize a bed of solid fuel, such as char, in a pressurized fluidized bed gasifier so as to produce a hot gas. The hot gas flows through a heat recovery steam generator so as to produce steam, which is expanded in a steam turbine so as to produce shaft power. A first portion of the hot gas from the heat recovery steam generator is expanded in the turbine section of the gas turbine so as to produce additional shaft power. A second portion of the hot gas from the heat recovery steam generator is then used to cool the turbine section of the gas turbine, after further cooling and filtering. Since none of the turbine cooling fluid is obtained by bleeding compressed air directly from the compressor, the mass flow of the hot gas flowing through the gasifier, and, therefore, the hot gas it produces is maximized, thereby maximizing steam generation in the heat recovery steam generator.

Growing community of inventors

Winter Springs, FL, United States of America

Hubertus Edward Paprotna