United Technologies Corporation

Sikorsky Aircraft Corporation

Carrier Corporation

Pratt-whitney Canada Corp

Raytheon Technologies Corporation

Lee A Hoffman

Zaffir A Chaudhry

Fanping Sun

Michael G McCaffrey

Lev Alexander Prociw

Jun Shi

Tahany Ibrahim El-Wardany

Andrzej Ernest Kuczek

David C Jarmon

Joel H Wagner

Joseph J Sangiovanni

Michael A Klecka

Brian Ernest Wake

Daniel V Viens

Robert H Dold

Peter F Lorber

Aleksandar Kojovic

Shaoluo L Butler

Sivakumar Gopalnarayanan

Fred W Kohlhepp

Jeffrey T Benoit

Steven A Lozyniak

David J Bombara

Robert A Grelotti

Joe J Liou

Jimmy Lih-Min Yeh

Hailing Wu

Seung Bum Kim

John F Zimmerman

Jimmy Lin-Min Yeh

Richard B Ferraro

Richard Jeremy Bedwell

Robert Morton

Richard J Bedwell

Sun Fanping

A system for modulating turbine blade tip clearance is provided. The system may comprise an actuation control system having at least one actuator configured to modulate turbine blade tip clearance between a turbine blade tip and a blade outer air seal (BOAS). Each actuator may be coupled to the BOAS. Each actuator may comprise a solid-state motion amplification device such as a flextensional actuator. The actuators may be configured to move the BOAS in a radial direction from a first position to a second position to control tip clearance.

System for modulating turbine blade tip clearance

An example peening tool includes at least one first roller having a peening surface disposed about and along a first core. At least a portion of the at least one first roller is configured to contact a component to be peened along a length. The length extends along at least a portion of the first core. The at least one first roller is configured to provide line contact on the component along the length. A profile of the at least one first roller is determined based on a profile of the component. The peening tool includes a backer disposed in register with the first plurality of rollers such that the first plurality of rollers moves with the backer during peening. The at least one first roller and the backer are configured to be arranged on opposing surfaces of the component. Peening models may predict peening parameters and controller settings.

Roll peening tooling and process

A device for controlling the pitch of a helicopter's rotor blade, the device having a BLDC motor based actuator; and at least one control surface operatively connected to the BLDC motor based actuator. The actuator and the control surface are preferably fully integrated into the interior profile of the rotor blade and are capable of controlling the PFC of the helicopter and improving HHC during operation by reducing noise and vibration. The motor is preferably a high power density motor incorporating rare earth permanent magnets connected to a roller/ball screw or planetary gear set to provide the right combination of force/torque, stroke and frequency.

Brushless direct current (BLDC) motor based linear or rotary actuator for helicopter rotor control

A reverse flow combustor has an inlet end. A flowpath extends downstream from the inlet end through a turn. The turn directs the flowpath radially inward and reversing an axial flow direction. A large exit duct (LED) is along the turn. A small exit duct (SED) is along the turn and joined by a joint to a mounting structure to resist separation in a first axial direction. The joint comprises: a first surface on the SED facing partially radially inward; and a mounting feature engaging the first surface.

Reverse flow combustor duct attachment

A braze-free connector suitable for use in a refrigeration system that includes a connector body having a circular opening passing therethrough. The opening has a converging section that tapers downwardly from the entrance to the opening toward the back of the opening. A ferrule is slidably mounted upon a refrigerant tube which is inserted into the opening to place a tapered collapsible section of the ferrule in contact with the tapered section of the opening. The non-collapsible section of the ferrule is keyed to a nut which in turn is mated with a male thread formed on the connector body whereby the collapsible section of the ferrule is forced into engagement with the refrigerant tube. A pressure sensitive sealant is pre-coated upon at least the collapsible section of the ferrule which is activated as the ferrule is forced into engagement with the refrigerant tube.

Braze-free connector utilizing a sealant coated ferrule

An actuation system for pivoting a flap on a helicopter rotor blade to reduce the interaction of the blade with the preceding blade vortex. The actuation system includes a fluid supply which is connected to first and second fluid supply lines. The fluid supply lines convey flows of pressurized fluid from the fluid supply to an actuator. The actuator includes a housing mounted within the rotor blade and having a channel formed in it. A butterfly shaft is pivotally mounted within the channel and has laterally extending arms which separate the channel into four lobes. A first port connects the first fluid supply line with two diametrically opposed lobes in the channel. A second port connects the second fluid supply line with the other two diametrically opposed lobes in the channel. A torque coupling is attached to the butterfly shaft and engaged with the flap such that rotation of the torque coupling produces concomitant rotation of the flap. The pressurization of the first fluid supply line causes the torque coupling to rotate in a first direction. The pressurization of the second supply fluid line causes the torque coupling to rotate in the opposite direction.

High torque actuation system for an active rotor control system

Growing community of inventors

Vernon, CT, United States of America

Lee A Hoffman