United Technologies Corporation

Siemens Energy, Inc.

Robert T Brooks

Marc J Muldoon

Tor W Sherwood

Meggan Harris

Harvey R Toppen

Yevgeniy P Shteyman

James S Marshall

David James Wiebe

Manish S Gurao

Timothy A Swanson

Brian Harry Terpos

Jonathan M Leagon

Robert Watson Spitzer

Carl T Elving

Matthew R Rader

Robert Angel

Scott W Smith

Meggan H Harris-Miller

Keith W Piersall

Ashley N Girdich

James Alfonso

Brian Micklos

Christopher Scogin

James Marshall

Meggan H Harris

A belly band seal for use in a multi-stage turbomachine having plural rotor disks includes a seal strip positionable in a space between a pair of arms defined by opposing portions of adjoining rotors. The seal strip includes opposite edges for locating in respective slots in end faces of said pair of arms. The belly band seal further includes an anti-rotation structure disposed on a radially inner surface of the seal strip. The anti-rotation structure is configured as a cantilever having a pivoted end fixed to the radially inner surface and a free end comprising a radially inwardly extending engagement member for removably positioning in a radial recess in one of the arms. The cantilever is configured so as to urge the engagement member toward the radial recess by spring action. The radial recess is configured to constrain a tangential movement of the engagement member upon being positioned therein.

Belly band seal with anti-rotation structure

A transition duct system () for routing a gas flow from a combustor () to the first stage () of a turbine section () in a combustion turbine engine (), wherein the transition duct system () includes one or more converging flow joint inserts () forming a trailing edge () at an intersection () between adjacent transition ducts () is disclosed. The transition duct system () may include a transition duct () having an internal passage () extending between an inlet () to an outlet () and may expel gases into the first stage turbine () with a tangential component. The converging flow joint insert () may be contained within a converging flow joint insert receiver () and disconnected from the transition duct bodies () by which the converging flow joint insert () is positioned. Being disconnected eliminates stress formation within the converging flow joint insert (), thereby enhancing the life of the insert. The converging flow joint insert () may be removable such that the insert () can be replaced once worn beyond design limits.

Converging flow joint insert system at an intersection between adjacent transitions extending between a combustor and a turbine assembly in a gas turbine engine

An adjustable transition duct support system for a transition duct that channels hot gases from a combustor exit to a gas turbine inlet of a turbine engine. The adjustable transition duct support system includes an adjustable forward transition flexible support assembly in contact with a transition duct body, whereby the forward transition flexible support assembly may be formed from a base extending toward the transition duct body and first and second side support arms extending from the base to the transition duct body. The first and second side support arms may be formed from a plurality of flex plates spaced from each other with spacers that provide rigidity in circumferential and radial directions and flexibility in an axial direction. The number of flex plates used may be varied to accommodate different turbine engines. The adjustable transition duct support system may have natural frequencies for circumferential and radial modes above two engine orders.

Transition support system for combustion transition ducts for turbine engines

A flange connection for an exhaust section of a gas turbine engine. The flange connection includes a stub flange attached to an exhaust manifold. The stub flange has a first axial face for engagement with the axial face of a cylinder flange extending radially from an exhaust cylinder. A plate structure attached to the cylinder flange is configured to provide axial retention of the stub flange to the axial face of the cylinder flange. The plate structure includes a resilient beam portion extending radially inwardly and engaging a second axial face of the stub flange. The stub flange is retained between the cylinder flange and the beam portion of the plate structure in an interference fit to provide three degrees of freedom of the stub flange relative to the exhaust cylinder.

Exhaust manifold flange connection

A gas turbine engine augmentor has a centerbody within a gas flowpath from upstream to downstream. The augmentor has upstream and downstream shell sections, a downstream rim of the upstream shell section meeting an upstream rim of the downstream shell section shell section. A plurality of vanes are positioned in the gas flowpath outboard of the centerbody. An augmentor spray bar fuel conduit extends through the centerbody and a first of the vanes to deliver fuel to the centerbody. A seal is mounted to the spray bar and positioned in a recess extending from at least one of the downstream rim of the upstream shell section and upstream rim of the downstream shell section shell section. The seal has a first portion and a second portion engaging the first portion in a backlocked interfitting.

Augmentor spray bar mounting

A rotational flow balance system includes an actuator system which controls operation of both a fan duct blocker ring and a modulated exhaust cooling ring through a kinematic system. The kinematic system is controlled by the single actuator system such that the modulated exhaust cooling ring will remain in a fixed position while the fan duct blocker ring can be moved to satisfy operational requirements.

Single actuator controlled rotational flow balance system

A gas turbine engine fueling system includes a number of spray bars having conduits extending through associated vanes. A number of fuel injector nozzles are along each conduit. Each of the nozzles are positioned to discharge an associated fuel stream from one of the sides of the associated vane. A number of wear members are each mounted relative to the associated one of the nozzles for a range of motion relative thereto. The wear members movably cooperate with the associated vane to accommodate operating deflection and/or tolerances of the spray bars and vanes.

Augmentor spray bars

A gas turbine engine augmentor has a centerbody within a gas flowpath from upstream to downstream. A plurality of vanes are positioned in the gas flowpath outboard of the centerbody. An augmenter fuel conduit extends through a first of the vanes to deliver fuel to the centerbody. An electrographitic carbon bushing guides and supports the augmentor fuel conduit.

Augmentor fuel conduit bushing

A method for improving the wear characteristics of a system for operating a variable vane comprising the steps of providing a trunnion connected to the variable vane via an vane platform and means for causing rotation of the trunnion, and positioning a thrust washer formed from a carbon material about a lower portion of the trunnion and in a space between the vane platform and an outer split case so that during operation of the system the space between the vane platform and the outer split case is maintained substantially constant and unwanted deflection of the vane is avoided.

Variable vane electro-graphic thrust washer

An apparatus for separating two flanges, comprising a first prying grip having at least one flange contact member, a second prying grip having at least one flange contact member; and means for separating the flange contact members.

Tooling provision for split cases

A method and shield assembly,for use in processing a flow directing assembly,such as a stator vane or rotor blade, is disclosed. Various details are developed for the construction of the shield assembly and for the method of masking the flow directing assembly. The shield assembly has a shield having two sides,and at least one tab,which extends from one of the sides and through the other side and is pressed against the other side. In one embodiment, the method includes exerting a force against the shield to block movement of the shield from the installed position. The shield assembly might include a locking member for this purpose which has a projection,which is attached to the shield or a locking member,which is not attached to the shield and which has a tab,which engages the shield and a projection,which engages the airfoil. Alternatively, the shield assembly might include a clamp,which presses the shield against the airfoil.

Method and assembly for masking a flow directing assembly

A locking member for engaging a shield,which is disposed during processing about an airfoil,of a flow directing assembly,, such as a stator vane or rotor blade, is disclosed. Various details are developed for the construction of the locking member. In one embodiment, the locking member is separate from the shield and has projections,that each engage an opening,in the airfoil and tabs,which engage an opening,in the shield. In another embodiment, the shield has a projection,which is attached to the shield.

Locking member for processing a flow directing assembly

A shield 40 for use in processing a flow directing assembly 10, such as a stator vane or rotor blade, is disclosed. Various construction details are developed for the shield. The shield has two sides 52, 56 and at least two tabs 56, 58 which each extend from one of the sides and through the other side.

Growing community of inventors

Chuluota, FL, United States of America

Robert T Brooks