United Technologies Corporation

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Raytheon Technologies Corporation

United Technologies Operations

Daniel W Major

Edward Torres

Gregory E Reinhardt

John C DiTomasso

Nathan F Champion

Paul Thomas Rembish

Barry William Spaulding

Donald Summers

William J Speers

Bernard W Pudvah

Joseph C Burge

Wiiliam J Iii Speers

William J Iii Speers

A gas turbine engine includes a fan that includes a plurality of fan blades rotatable about an axis. An on-wing portion includes a compressor section and a combustor that is in fluid communication with the compressor section. A turbine section is in fluid communication with the combustor. A core flow path is arranged within a core nacelle. The fan is arranged upstream from the core flow path. A fan drive gear system module is coupled to the turbine section for rotating the fan about the axis. A connector assembly including first and second members respectively is secured to the on-wing portion and the fan drive gear system module. The first and second members are removably secured to one another by radially extending fasteners. The first members are connected to an on-wing portion of the gas turbine engine and the second members are connected to the fan drive gear system module. The fasteners are accessible through the bypass flow path.

Fan drive gear system module and inlet guide vane coupling mechanism

A connection assembly for securing a fan drive gear system module within a gas turbine engine includes first and second members removably secured to one another by radially extending fasteners.

A stator assembly for a turbine engine includes a support structure, such as an outer case, providing a bore. A non-metallic bushing is arranged in the bore and extends radially between inner and outer diameters providing a one-piece structure. The outer diameter of the bushing engages the bore in a press-fit relationship, in one example. A stator includes a trunnion arranged within and engaging the bushing inner diameter. In one example, the non-metallic bushing is constructed from an electrographitic carbon. The bushing is installed into the bore such that an end of the bushing is generally flush with or recessed from a wall on the support structure.

Variable stator vane assembly for a turbine engine

An inner shroud assembly includes an aft core segment mountable to a forward core segment to support a multiple of vanes for rotational movement relative thereto. A shroud backing plate segment engageable with the aft core segment and at least one fastener which passes through the shroud backing plate, the aft core segment and the forward core segment.

Inner diameter shroud assembly for variable inlet guide vane structure in a gas turbine engine

An inner diameter shroud for receiving an inner diameter base portion of a rotatable vane in a gas turbine engine has a single piece channel and a core. The channel has a leading edge wall, an inner diameter wall, a trailing edge wall, a radial outer surface, and at least two axial projections. The axial projections prevent radial movement of the core. The core has an outer radial surface that generally aligns with the radial outer surface of the channel. The core is movable in the channel in a circumferential direction and is configured to rotatably retain the inner diameter base portion of the rotatable vane.

Single channel inner diameter shroud with lightweight inner core

A variable vane arm has a hook portion comprising a radially inner leg connected to a radially outer leg by an arcuate connection, and an actuation lever extending from the hook portion. The hook portion and actuation lever are formed from a singular piece of material.

Scalable high pressure compressor variable vane actuation arm

An inner air seal carrier for use in a gas turbine engine having an inlet guide vane surge retainer comprises a body, a stationary sealing element and an outcropping. The body secures around an inlet guide vane inner diameter shroud. The stationary sealing element is disposed on a radially inward face of the body for engaging with a rotatable sealing element of a compressor rotor. The outcropping is positioned on the radially inward face of the body forward of the stationary sealing element for engaging with the surge retainer.

Inlet guide vane inner air seal surge retaining mechanism

A turbine engine variable stator vane includes a platform having a circumference adjoining opposing surfaces. A trunnion extends from one of the opposing surfaces. An airfoil is supported on the other of the opposing surfaces opposite the trunnion. The airfoil includes leading and trailing edges. An overhanging portion of the airfoil, which includes the trailing edge, extends beyond the circumference. A fillet joins the airfoil and the other opposing surface and extends along the other opposing surface in a lateral direction beyond the circumference toward the trailing edge. In one example, the fillet is provided about the entire perimeter of the airfoil. The airfoil includes pressure and suction sides. The circumference includes a relief cut extending from the suction side and adjoining a notch in the circumference to form an apex overlying the end surface.

Turbine engine variable stator vane

A shroud for supporting a variable vane in a compressor section for a gas turbine engine includes a pair of components which are secured together by a threaded fastener extending into a blind hole in one of the two components. Additional material forms on the component which includes the blind hole extends beyond a pivot axis for the vane such that there is an increased length of engagement between the threaded fastener and the blind hole. The blind hole eliminates the need for multiple nuts and reduces the radial height of the shroud to save additional weight.

Small radial profile shroud for variable vane structure in a gas turbine engine

A barbed tape includes a central supporting portion and a plurality of barb clusters disposed at spaced apart locations along the central supporting portion, each barb cluster having first and second pairs of oppositely extending substantially planar barbs disposed on opposite edges of the central supporting portion and connected thereto, the barbs having a cross section which is at least partially arcuate, whereby the barbs are substantially stiffened against bending. A process for forming a barbed tape having stiffened barbs includes the steps of providing a barbed tape having a central supporting portion and a plurality of barb clusters disposed at spaced apart locations along the central supporting portion, each barb cluster having first and second pairs of oppositely extending substantially planar barbs disposed on opposite edges of the said supporting portion and connected thereto, and roll forming the barb clusters so as to provide the barbs with a cross section which is at least partially arcuate, whereby the barbs are substantially stiffened against bending.

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Middletown, CT, United States of America

Daniel W Major