Other

United Technologies Corporation

Raytheon Technologies Corporation

Rafael A Perez

Edward F Pietraszkiewicz

Tracy A Propheter-Hinckley

Efrain E Vega

Nicholas M LoRicco

Christopher Corcoran

Anton G Banks

Seth J Thomen

Eleanor D Kaufman

Ricardo Gonzalez

Jaime G Ghigliotty

Donald Kastel

Andres E Diaz

Juan Pablo Lopez

Pedro L Castaneda

Nestor A Alvarez

Jamie G Ghigliotty

Vane assemblies for turbine engines are described. The vane assemblies include a vane having an internal cavity and a vane platform and a vane rail defining, in part, an outer diameter supply cavity. A blade outer air seal support (BOAS support) is arranged adjacent the vane and engages with a portion of the vane, the blade outer air seal support having BOAS support rail, and a BOAS supported on the BOAS support and engaging with a portion of the vane. The BOAS support includes a first cooling flow aperture configured to enable a cooling flow to cool at least the BOAS and a second cooling flow aperture formed in the BOAS support rail. The vane rail includes a third cooling flow aperture to form a cooling flow path through the second cooling flow aperture and the third cooling flow aperture to fluidly connect to the outer diameter supply cavity.

Turbine vane having dual source cooling

A turbine blade for a gas turbine engine. The turbine blade having a plurality of cooling holes defined therein, at least some of the plurality of cooling holes being located on a suction side of an airfoil of the turbine blade and in fluid communication with an internal cavity of the turbine blade; and wherein the at least some of the plurality of cooling holes are located in the airfoil according to the coordinates of Tables 1 and/or 2.

Turbine blade cooling hole arrangement

An airfoil for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, an airfoil body and a cooling circuit disposed inside the airfoil body and including a leading edge cavity with a first portion extending from a radially inner wall to a radially outer wall of the airfoil body and a second portion that extends from a leading edge inner wall to a trailing edge inner wall of the airfoil body. The cooling circuit is configured to communicate cooling airflow through the first portion and the second portion prior to exiting the leading edge cavity into a second cavity of the cooling circuit.

Gas turbine engine airfoil cooling circuit

The present disclosure relates to cooling systems for turbine stators. A stator may include a vane platform. A ducting plate may be coupled to the vane platform. The ducting plate and the vane platform may form a cooling chamber between the ducting plate and the vane platform. The ducting plate may include an inlet adjacent to a leading edge of the vane platform. The vane platform may include an outlet adjacent to a trailing edge of the vane platform. The ducting plate may be configured to channel cooling air through the cooling chamber from the leading edge to the trailing edge.

Ducting platform cover plate

A rotor blade comprises a root section, an airfoil section, a leading edge cooling cavity, an intermediate cooling cavity, and a trailing edge cooling cavity. The leading edge, intermediate, and trailing edge cooling cavities each extend spanwise through the airfoil section from a coolant inlet passage in the root section, and each terminate proximate the airfoil tip.

Low pressure loss cooled blade

An airfoil for a gas turbine engine according to one exemplary embodiment includes an airfoil body that extends between a leading edge and a trailing edge. A cooling circuit can be defined within the airfoil body. The cooling circuit can include at least one trip strip disposed within a cavity of the cooling circuit between a leading edge inner wall and a first rib. The at least one trip strip can include an increasing height in a direction from the first rib toward the leading edge inner wall.

An airfoil for a gas turbine engine includes an airfoil body and a cooling circuit defined within the airfoil body. The cooling circuit includes at least a first cavity in fluid communication with a second cavity. A first portion of the first cavity extends between an outer diameter and an inner diameter of the airfoil body and a second portion of the first cavity extends across a space between a leading edge and a trailing edge of the airfoil body.

A clipper for cutting and severing a portion of bait material preventing direct contact of a user with the former. The two elongated pivotally mounted members include cutting assemblies ends that cooperate to come towards each other in a substantially parallel fashion. Peripheral walls with distal sharpened edges have to cut into a bait severing a portion that is lodged between complementing cavities formed by the peripheral walls. Slots in the base plates extend towards their respective centers upon which the peripheral wall are perpendicularly mounted permit a user to manipulate a fishing hook. The hook is removed through one of the cutouts in the peripheral walls that coincide with the entrance to the slots. A user can then hold the bait portion with one hand while safely manipulating the hook with the other hand to set his/her fishing bait.

Bait clipper

A bale manger which includes a bed and rear wall extending substantially normal to the bed. A front wall is opposed to and spaced from the rear wall. The front wall is pivotally connected about a pivot to an end portion of the bed and has a bend therein to permit a first portion of the front wall remote from the bed to lie in a plane parallel to and below the bed when the front wall is appropriately pivoted. A second portion of the front wall between the bed and the first portion of the front wall makes an obtuse angle with the first portion. The bed is elevated. A pair of side walls which are preferably secured to the bed make an enclosure with the bed, front wall and rear wall when the front wall is pivoted in a direction toward the rear wall. The front wall is pivoted by a structure which causes the front wall to rotate about the pivot toward the rear wall. A preferred such structure is a pulley secured to the rear wall and a cable securable to the front wall and rotatable by the pulley.

Bale manger

An illuminated balloon assembly including a balloon having a main body disposed in surrounding relation to an interior gas chamber and a neck portion integrally formed therewith to facilitate filling of gas within the interior chamber. An electric lamp is fixedly attached to an outer surface of the balloon body so as to direct light through the interior chamber effectively illuminating a translucent design on at least a portion of the balloon body. A power source is electrically interconnected with the electric lamp for energizing thereof and may be attached to the balloon body in a combined unit with the electric lamp or separately on the end of an interconnecting stick or cord connected to and extending from the neck portion.

Illuminated balloon assembly

An illuminated balloon having a front face and a rear face sealed together about an outer peripheral edge in surrounding relation to an interior gas chamber, and a neck portion integrally formed therewith to facilitate filling of gas within the interior chamber. An electric lamp is fixedly attached to an outer surface of the balloon so as to direct light through the interior chamber effectively illuminating a design on at least one of the faces of the balloon. A battery pack is electrically interconnected to the electric lamp by a pair of substantially thin gauge wires intertwined to form a cord extending therebetween.

Illuminated balloon

A cutting element for being longitudinally connected to form a saw which can cut in two or four planes and 'to and fro' because of its self-cleaning action during use provided by rotating a blade 90.degree. in relation to its connected preceeding blade.

Growing community of inventors

Arecibo, Puerto Rico

Rafael A Perez