United Technologies Corporation

Raytheon Technologies Corporation

Audi Ag

Utc Fuel Cells, LLC

David A Niezelski

Timothy J Jennings

Jeffrey T Morton

Robert A Love

Nicholas M LoRicco

Joshua Daniel Winn

Bret M Teller

Alex J Schneider

Jeffery G Lake

Jason Bennett Blydenburgh

Thomas N Slavens

Ghislain Plante

Jeffrey S Beattie

Panagiota Tsifourdaris

John H Whiton

Daniel Lecuyer

Thomas Harry Madden

Michael Leslie Clyde Papple

Domenico Di Florio

Alex J Simpson

Rene Paquet

Jeremy P Meyers

John McBrien

Ryan Lundgreen

Parth Jariwala

John R Battye

Kristoffer H Ridgeway

Nileshkumar Trambaklal Dave

Sushant S Bhadange

Richard R Phillips

Richard Horace Shaw

Stephen P Victor

Guillaume Michael Kurczko Brousseau

Edward G Adamski

Francois Caron

XingYun Haggard

Edward Gordon Schaub

Maura M Vigliano

A turbine blade for a gas turbine engine. The turbine blade having a plurality of cooling holes defined therein, wherein the plurality of cooling holes are located in the turbine blade according to the coordinates of Table 1 and at least some of the plurality of cooling holes are located in an airfoil of the turbine blade.

Turbine blade cooling hole arrangement

A turbomachine airfoil element comprises an airfoil having: an inboard end; an outboard end; a leading edge; a trailing edge; a pressure side; and a suction side. A span between the inboard end and the outboard end is 1.75-2.20 inches. A chord length at 50% span is 1.05-1.35 inches. At least two of: a first mode resonance frequency is 2400&#xb1;10% Hz; a second mode resonance frequency is 4950&#xb1;10% Hz; a third mode resonance frequency is 7800&#xb1;10% Hz; a fourth mode resonance frequency is 8700&#xb1;10% Hz; and a fifth mode resonance frequency is 12500&#xb1;10% Hz.

Turbomachine blade

Airfoils for gas turbine engines are described. The airfoils include an airfoil body extending between a platform and a tip, the airfoil body having a leading edge, a trailing edge, a pressure side, and a suction side, a serpentine cavity formed within the airfoil body and having an up-pass serpentine cavity, a down-pass serpentine cavity, and a trailing edge cavity, and a dead-end tip flag cavity extending in a direction between the leading edge and the trailing edge, the dead-end tip flag cavity arrange between the serpentine cavity and the tip, wherein the dead-end tip flag cavity ends at a dead-end wall located at a position between the leading edge and the trailing edge of the airfoil body.

Airfoil having dead-end tip flag cavity

A turbine blade for a gas turbine engine having a plurality of cooling holes defined therein, the plurality of cooling holes are located in an airfoil of the turbine blade according to the coordinates of Table 1.

A turbine blade for a gas turbine engine having an airfoil to platform fillet, wherein the fillet is contoured in accordance with the coordinates of Table 1.

Turbine blade with contoured fillet

An exemplary fuel cell device includes a cell stack assembly having a plurality of fuel cells. A vapor barrier tape is wrapped around at least a portion of an exterior of the cell stack assembly. An exemplary method of managing moisture within a fuel cell stack assembly includes covering at least a portion of an exterior of the cell stack assembly with a vapor barrier tape to thereby maintain moisture within the cell stack assembly.

Fuel cell device and method of managing moisture within a fuel cell device

A component according to an exemplary aspect of the present disclosure includes, among other things, a wall and at least one rib that protrudes from the wall and extends to a rib end, the rib end having a curved transition portion near a location where the at least one rib meets the wall.

Gas turbine engine component having contoured rib end

A method of manufacturing a porous structure for a fuel cell is disclosed. The method includes providing the porous structure, and processing the porous structure to selectively produce a non-porous region on the porous structure. In one example, the non-porous region is provided at the perimeter of the porous structure, an edge of an internal manifold and/or a surface or recess that supports a seal or gasket. The non-porous region has a porosity that is less than the porosity of the porous structure. The non-porous region prevents undesired leakage of fluid from the porous structure and prevents migration of adhesive associated with the seals.

Selectively sealing fuel cell porous plate

Aspects of the disclosure are directed to a damper configured to be located in a cavity formed between first and second bases configured to seat respective first and second airfoils, the damper having a first face and a second face, where an aspect ratio between the first face and the second face ensures that the damper is installed in the cavity in accordance with a predetermined orientation.

Damper seal installation features

The present disclosure provides systems for preventing improper installation of a damper seal. In various embodiments, an airfoil assembly may comprise a platform, an airfoil extending from the platform, and a platform tab. The airfoil may comprise a gaspath face and a non-gaspath face. The non-gaspath face may at least partially define a cavity. The airfoil may comprise a pressure side and a suction side. The platform tab may be located adjacent to the suction side of the airfoil. The platform tab may extend from the platform in the opposite direction as the airfoil and may be configured to prevent a damper seal tab from being inserted radially inwards of the platform tab.

Installation fault tolerant damper

A fuel cell plate is provided that includes a flow field having a plurality of channels each with an inlet end, and a header in fluid communication with the inlet ends. The header has at least one restricted flow region in which fluid flow is restricted to the inlet ends of a set of channels of the flow field and at least some of the plurality of channels include a pressure drop feature that is configured to increase fluid flow to the set of channels.

Fuel cell plate flow field

Fuel cell systems () and related methods for limiting fuel cell slippage are provided. A stacked plurality of adjacent fuel cells () collectively forming a fuel cell stack (). The fuel cells each include a pair of first and second plates () at respective opposite ends thereof. A first fuel cell has a first plate () in engagement with a second plate () of a second fuel cell adjacent to the first fuel cell. A slip mitigation arrangement () between at least one of the pairs of the first and second fuel cells comprises first and second seats () recessed in the engagement surfaces of the first and second conductive plates respectively, and a key member () having opposite ends seated in the first and the second recessed seats such that relative movement between the first and the second fuel cells is limited.

Fuel cell systems and related arrangements for limiting relative motion between fuel cells

Fuel cell systems () and related methods for limiting fuel cell slippage are provided. A stacked plurality of adjacent fuel cells () collectively forming a fuel cell stack (). The fuel cells each include a pair of first and second plates () at respective opposite ends thereof. A first fuel cell has a first plate (&#x2033;) in engagement with a second plate () of a second fuel cell adjacent to the first fuel cell. A slip mitigation arrangement () between at least one of the pairs of the first and second fuel cells comprises first and second seats () recessed in the engagement surfaces of the first and second conductive plates respectively, and a key member () having opposite ends seated in the first and the second recessed seats such that relative movement between the first and the second fuel cells is limited.

A PEM fuel cell assembly includes cooler plates () with internal coolant manifolds () isolated from the cell stack assembly by an isolation gap () to minimize the risk of contamination of the cells by antifreeze. The internal coolant manifolds are formed by seal assemblies (), each disposed between inlet or outlet openings () in projections () of each cooler plate extending outwardly from the fuel cell planform () to provide a gap (), which may be used as an air turn manifold. Flanges () with through holes () may receive tie rods to assist assembly of a fuel cell stack with the cooler plate.

PEM fuel cell stack assembly with isolated internal coolant manifold

An electrode for use in a rotary electrical discharge machining (EDM) device for producing at least one curved hole in an article includes at least one curved tooth. The curved tooth lies in a plane. A perpendicular line to that plane is parallel to the axis of rotation on the rotary EDM device. At least one curved cooling hole is machined in the article.

Growing community of inventors

Manchester, CT, United States of America

David A Niezelski