United Technologies Corporation

Raytheon Technologies Corporation

Rtx Corporation

Edwin Otero

Jeffrey Michael Jacques

Michael G McCaffrey

John R Farris

Ross Wilson

Elizabeth F Vinson

John E Paul

Theodore W Hall

Brandon W Spangler

John J Korzendorfer

Alan W Stoner

Daniel A Snyder

Kyle C Lana

Patrick Strong

Scott Daniel Virkler

Jonathan Perry Sandoval

Jaimie Taraskevich

Di Wu

Tracy A Propheter-Hinckley

Mark F Zelesky

Raymond C Surace

Bryan P Dube

Wendell V Twelves

Evan J Butcher

Jose R Paulino

Eric A Hudson

Shawn J Gregg

Lexia Kironn

Alan C Barron

David R Pack

Jeffrey J DeGray

Emma J Place

Mark A Boeke

Craig R McGarrah

Mohamed Hassan

Timothy Charles Nash

Sarah Riley

Edward R Bareiss

Jaimie Schweitzer

Tracy A Propheter

Guillermo J Fernandez

John W Korzendorfer

Andrew Correia

Bernard Joseph Reilly, Iii

William R Hackbarth, Ii

Jr Wendell V Twelves

Jeffrey J Degray

Kyle Charles Lana

John R Korzendorfer

An attachment root for a blade includes a symmetric serration profile with multiple lobes. Contact surfaces of each lobe form equal contact angles with a line normal to a symmetry plane of the serration profile. Non-contact surfaces of lobes form angles greater than three degrees relative to the line that increase in a radially inward direction.

Turbine airfoil attachment with serration profile

A seal for a gas turbine engine includes a full hoop outer ring, a shoe coupled to the full hoop outer ring via an inner beam and an outer beam, and a wave spring in contact with at least one of the inner beam or the outer beam.

Non-contacting dynamic seal

A seal support structure is provided for a circumferential seal. In one embodiment, the seal support structure includes an engine support structure, a seal support, and a shoulder joining the engine support and seal support. The shoulder offsets the engine support from the seal support, and the shoulder and the seal support structure are configured to dampen vibration for the circumferential seal. The seal support structure may employ one or more dampening elements or materials to interoperate with a seal support structure to dampen vibration to a seal system.

Seal support structure for a circumferential seal of a gas turbine engine

A seal ring system is provided. The seal ring system comprises a segment defining a slot, a pedal along the slot, and an opening offset from the slot. A retention fastener may be disposed in the opening. A seal ring system is also provided comprising a first segment defining a first opening, a second segment defining a second opening, and a retention fastener extending through the first and second openings. The retention fastener configured to allow relative radial movement of the first segment and the second segment. A seal is further provided comprising a seal ring having a central axis, a petal extending radially inward with respect to the central axis of the seal ring, and a sealing disk axially proximate the seal ring. The sealing disk may have a seal shoe configured as a primary seal. The petal may extend toward the seal shoe.

Seal ring

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 1.35-1.65 inches. A chord length at 50% span is 1.20-1.60 inches. At least two of: a first mode resonance frequency is 2858&#xb1;10% Hz; a second mode resonance frequency is 4916&#xb1;10% Hz; a third mode resonance frequency is 7160&#xb1;10% Hz; a fourth mode resonance frequency is 10268&#xb1;10% Hz; a fifth mode resonance frequency is 14235&#xb1;10% Hz; and a sixth mode resonance frequency is 15088&#xb1;10% Hz.

Turbomachine blade

A gas turbine engine component includes a structure including spaced apart first and second exterior walls that extend in a first direction to an endwall. The first and second exterior walls are joined at the endwall to provide a cooling cavity. A wishbone baffle is arranged in the cooling cavity and includes first and second interior walls respectively adjacent to the first and second exterior walls. The first and second interior walls extend in the first direction to and are joined by an apex to provide a first cavity. The wishbone baffle separates the first cavity from a second cavity provided between the apex and the endwall.

Gas turbine engine airfoil with wishbone baffle cooling scheme

An example turbine includes a turbine disk and a turbine blade. The turbine disk includes a plurality of lugs and a plurality of slots. Each of the plurality of lugs is located between two of the plurality of slots. Each of the plurality of lugs includes a tab that extends radially outwardly from an end of the lug. The tab has a first section having an upper surface and a second section having an upper surface. The upper surface of the first section is inclined greater than the upper surface of the second section, and the upper surface of the first section of the tab defines a contour. The turbine blade includes a root received in one of the plurality of slots and a platform, and the platform has a lower surface defining a contour. When the turbine blade is received in one of the plurality of slots, the lower surface of the platform is located above a portion of the upper surface of the first section of the tab, and the contour of the upper surface of the first section of the tab matches the contour of the lower surface of the platform.

Turbine blade damper seal

Non-contacting dynamic seals having wave springs are disclosed herein. A non-contacting dynamic seal may have a shoe coupled to an outer ring by an inner beam and an outer beam. A wave spring may be located between the inner beam and the outer beam, between the shoe and the inner beam, or between the outer beam and the outer ring. The wave spring may damp vibrations in the inner beam and the outer beam.

A component for a gas turbine engine is disclosed. The component includes a platform and a rail having an outer radial surface and an inner radial surface, with the inner radial surface connected to the platform. The rail includes a plurality of apertures spaced circumferentially between the outer radial surface and the inner radial surface, the apertures disposed to form a truss-like structure.

Support rail truss for gas turbine engines

A gas turbine engine component includes spaced apart walls that provide a cooling passage that extends in a first direction. A cross-over rib joins the walls and extends along the first direction. The cross-over rib has holes that extend in a second direction transverse to the first direction. A row of at least one pedestal joins the walls and extends along the first direction. The row and the cross-over rib overlap one another in the second direction.

Gas turbine engine airfoil crossover and pedestal rib cooling arrangement

The present disclosure relates to sealing systems for gas turbine engines. In one embodiment, a seal support structure for a gas turbine engine includes a seal support configured to retain a circumferential seal and an engine support configured for mounting the seal support structure to a gas turbine engine mount. The engine support includes at least one channel configured to provide radial movement of the seal support structure and circumferential retention of the seal support. Another embodiment is directed to a sealing system including a circumferential seal and seal support structure configured to provide radial movement.

Seal support structure

A method of manufacturing an airfoil. The method includes fixing the airfoil in a workpiece space, detecting a position of the airfoil in the workpiece space using a force-sensing element, and removing material from the airfoil to reduce a dimension of the airfoil. In various embodiments, detecting the position of the airfoil includes moving the force-sensing element across a surface of the airfoil. For example, the surface of the airfoil may be a first surface, wherein removing material from the airfoil to reduce the dimension of the airfoil comprises removing material from a second surface of the airfoil opposite the first surface. Removing material from the second surface of the airfoil may be performed without moving the force-sensing element across the second surface of the airfoil.

Airfoil aerodynamics

An airfoil for use with a gas turbine engine includes a pressure side wall. The airfoil further includes a suction side wall configured to be exposed to less pressure than the pressure side wall during operation of the gas turbine engine. The airfoil also includes a plurality of ribs defining multiple air passages including at least one triangular air passage partially defined by at least one of the pressure side wall or the suction side wall, and at least one internal air passage bordered on at least three sides by at least two of the plurality of ribs.

Modified structural truss for airfoils

Growing community of inventors

Southington, CT, United States of America

Edwin Otero