Siemens Aktiengesellschaft

General Electric Company

Siemens Energy, Inc.

Other

Eric Joseph Schroeder

Ching-Pang Lee

Kok-Mun Tham

Paul Hadley Vitt

Jae Y Um

Erik Johnson

Zhengxiang Pu

Christopher Ryan Johnson

Kirk Douglas Gallier

Aspi Rustom Wadia

John Joseph Marra

Samuel R Miller, Jr

Anthony Waywood

Wayne J McDonald

Gerald L Hillier

Mohamed Abdullah

Jamie Meeroff

Timothy John Swenson

Carlos Gilberto Fernandez-Soto

Christian X Campbell

Gm Salam Azad

Nicholas F Martin, Jr

David Perveiler

Zhihong Gao

Thomas Joseph Lipinski

Manjit Shivanand

Ralph W Matthews

Dustin Jaime Muller

Steven Coppess

Kahwai G Muriithi

Carlos Fernandez

Diffuser apparatus for turbine frames and outlet guide vanes are disclosed. An example diffuser is integrated into a turbine engine. The example diffuser includes a plurality of struts extending between an inner portion and an outer portion of the turbine engine; and a plurality of flowpath surfaces supported by the plurality of struts. The example plurality of flowpath surfaces extends circumferentially within the turbine engine at a plurality of radial spans to control diffusion of air flow within the turbine engine.

Advanced aero diffusers for turbine frames and outlet guide vanes

A turbine engine and method of operating includes an engine core with a compressor, a combustor, and a turbine in axial flow arrangement. A flow path extends through the engine core from the compressor to the turbine to define a flow direction for a working airflow through the engine core.

Turbine engine with shockwave attenuation

Aspects of the disclosure generally relate to a turbine engine and method of operating a turbine engine having an engine core including a compressor, combustor, and turbine in axial flow arrangement, whereby a working airflow passes through the engine core from the compressor to the turbine to define a flow direction through the engine core. The method includes generating a shockwave in the working airflow that propagates in the flow direction, and at least partially attenuating the shockwave.

A turbine blade is described herein, the turbine blade including a blade root, a blade tip, and an airfoil extending between the blade root and the blade tip. The airfoil has opposite pressure and suction sides extending between a forward leading edge and an aft trailing edge of the airfoil, and a maximum thickness located between the leading edge and the trailing edge. The blade tip includes a winglet extending laterally outward from at least one of the pressure side and the suction side from a leading point between the leading edge and the maximum thickness aftward to a trailing point between the maximum thickness and the trailing edge.

Method and system for improving turbine blade performance

A core structure () includes a first core element () including a leading edge section (), a tip section (), and a turn section () joining the leading edge and tip sections (). The first core element () is adapted to be used to form a leading edge cooling circuit () in a gas turbine engine airfoil (). The leading edge cooling circuit () includes a cooling fluid passage () having a leading edge portion () formed by the first core element leading edge section (), a tip portion () formed by the first core element tip section (), and a turn portion () formed by the first core element turn section (). Each of the leading edge portion (), the tip portion (), and the turn portion () of the cooling fluid passage () are formed concurrently in the airfoil () by the first core element ().

Gas turbine airfoil including integrated leading edge and tip cooling fluid passage and core structure used for forming such an airfoil

Turbine and compressor casing/housing abradable component embodiments for turbine engines, have abradable surfaces with asymmetric forward and aft ridge surface area density. The forward ridges have greater surface area density than the aft ridges to compensate for greater ridge erosion in the forward zone during engine operation and reduce blade tip wear in the aft zone. Some abradable component embodiments increase forward zone ridge surface area density by incorporating wider ridges than those in the aft zone.

Turbine abradable layer with compound angle, asymmetric surface area ridge and groove pattern

An airfoil () for a gas turbine engine in which the airfoil () includes an internal cooling system () with one or more internal cavities having an insert () contained within an aft cooling cavity () to form nearwall cooling channels having enhanced flow patterns is disclosed. The flow of cooling fluids in the nearwall cooling channels may be controlled via a plurality of cooling fluid flow controllers () extending from the outer wall () forming the generally hollow elongated airfoil (). The cooling fluid flow controllers () may be collected into spanwise extending rows. In at least one embodiment, the cooling fluid flow controllers () may be positioned within a pressure side nearwall cooling channel () and a suction side nearwall cooling channel () that are both in fluid communication with a trailing edge channel (). The trailing edge channel () may also include cooling fluid flow controllers () extending between the outer walls () forming the pressure and suction sides.

Internal cooling system with insert forming nearwall cooling channels in an aft cooling cavity of an airfoil usable in a gas turbine engine

An airfoil () for a gas turbine engine in which the airfoil () includes an internal cooling system () with one or more internal cavities () having an insert () contained therein that forms nearwall cooling channels () having enhanced flow patterns is disclosed. The flow of cooling fluids in the nearwall cooling channels () may be controlled via a plurality of cooling fluid flow controllers () extending from the outer wall () forming the generally hollow elongated airfoil (). The cooling fluid flow controllers () may be collected into spanwise extending rows (), and the internal cooling system () may include one or more bypass flow reducers () extending from the insert () toward the outer wall () to direct the cooling fluids through the channels () created by the cooling fluid flow controllers (), thereby increasing the effectiveness of the internal cooling system ().

Internal cooling system with insert forming nearwall cooling channels in midchord cooling cavities of a gas turbine airfoil

A seal assembly between a disc cavity and a hot gas path in a gas turbine engine includes a stationary vane assembly and a rotating blade assembly axially upstream from the vane assembly. A platform of the blade assembly has a radially outwardly facing first surface, an axially downstream facing second surface defining an aft plane, and a plurality of grooves extending into the second surface such that the grooves are recessed from the aft plane The grooves are arranged such that a circumferential space is defined between adjacent grooves During operation of the engine, the grooves impart a circumferential velocity component to purge air flowing out of a disc cavity through the grooves to guide the purge air toward a hot gas path such that the purge air flows in a desired direction with reference to a direction of hot gas flow through the hot gas path.

Seal assembly including grooves in an aft facing side of a platform in a gas turbine engine

An outer rim seal arrangement (), including: an annular rim () centered about a longitudinal axis () of a rotor disc (), extending fore and having a fore-end (), an outward-facing surface (), and an inward-facing surface (); a lower angel wing () extending aft from a base of a turbine blade () and having an aft end () disposed radially inward of the rim inward-facing surface to define a lower angel wing seal gap (); an upper angel wing () extending aft from the turbine blade base and having an aft end () disposed radially outward of the rim outward-facing surface to define a upper angel wing seal gap (); and guide vanes () disposed on the rim inward-facing surface in the lower angel wing seal gap. Pumping fins () may be disposed on the upper angel wing seal aft end in the upper angel wing seal gap.

Aft outer rim seal arrangement

A gas turbine engine including: an ambient-air cooling circuit () having a cooling channel () disposed in a turbine blade () and in fluid communication with a source () of ambient air: and an pre-swirler (), the pre-swirler having: an inner shroud (); an outer shroud (); and a plurality of guide vanes (), each spanning from the inner shroud to the outer shroud. Circumferentially adjacent guide vanes () define respective nozzles () there between. Forces created by a rotation of the turbine blade motivate ambient air through the cooling circuit. The pre-swirler is configured to impart swirl to ambient air drawn through the nozzles and to direct the swirled ambient air toward a base of the turbine blade. The end walls () of the pre-swirler may be contoured.

Ambient air cooling arrangement having a pre-swirler for gas turbine engine blade cooling

A gas turbine engine, including: a plurality of blades () assembled into an annular row of blades and partly defining a hot gas path () and a cooling fluid path (), wherein the cooling fluid path extends from a rotor cavity () to the hot gas path; an angel wing assembly () disposed on a side () of a base () of the row of blades; and pumping features () distributed about the angel wing assembly configured to impart, at a narrowest gap () of the cooling fluid path, motion to a flow of cooling fluid flowing there through. The plurality of pumping features, the angel wing assembly, and the base of the row of blades are effective to produce a helical motion to the flow of cooling fluid as it enters the hot gas path.

Turbine blade angel wing with pumping features

A doll has a body and an item that is sized to be releasably attached to the body. The item includes an attachment portion that is releasably engaged by engaging structure on the body. Covering structure is utilized to cover the engaging structure when the item is not attached to it. The engaging structure may include hook material and both the attachment structure and covering structure may include loop material. The doll may be outfitted with a uniform corresponding to a particular sport. The item may be a piece of sporting equipment proportionally sized relative to the doll and corresponding to the sport of the uniform. A kit may be provided for creating a sporting environment. The kit has an embodiment of the above-described doll, at least one item of sporting equipment proportionately sized relative to the doll, and a box for containing the doll and the sporting equipment. A uniform for the doll may also be included with the kit. The above-described attaching structure is on the sporting equipment. Adapting structure such as a perforated pattern on at least one surface of the box is used to create the sporting environment for interacting with the doll and sporting equipment.

Growing community of inventors

Loveland, OH, United States of America

Eric Joseph Schroeder