United Technologies Corporation

Raytheon Technologies Corporation

Jonathan Ariel Scott

Conway Chuong

Matthew Budnick

Darren M Smith

Jorge I Farah

Tuan David Vo

William J Yeager

Chris Bates

Darrell Weidner

John E Wilber

Steven J Bauer

Kalpendu J Parekh

David T Feindel

Kevin W White

Henry K Webster

Jason David Liles

Randall J Brown

Albert Veninger

John J Henderson

Larry B Hawke

Alan D Lees

Ralph D Harris

Chuong Conway

An assembly for a gas turbine engine includes a first casing, a second casing, and struts extending from the first casing to support the second casing. The assembly further includes a fairing and a multi-piece heat shield assembly. The fairing is disposed between the first casing and the second casing and around each of the struts. The multi-piece heat shield assembly includes a first shield extending between the first casing and the fairing, and a second shield extending between the fairing and the first casing. The multi-piece heat shield assembly further includes a third shield extending between the fairing and the second casing, and fourth and fifth heat shields extending from the third heat shield between the fairing and each of the struts.

Multi-piece heat shield

A system and method for coupling cases associated with an engine of an aircraft. A first case includes a first plurality of threads. A second case includes a second plurality of threads. A coupler includes a third plurality of threads and a fourth plurality of threads. An interface is configured to align the first case and the second case before the first plurality of threads engage the third plurality of threads or the second plurality of threads engage the fourth plurality of threads.

Case coupling and assembly

An annular finger seal includes a base portion defining a base edge of the annular finger seal and having a center pass-through aperture. The base edge may be substantially continuous. The annular finger seal may also include a finger portion defining a finger edge of the annular finger seal and including a plurality of fingers. The finger edge may be segmented by gaps disposed between adjacent fingers of the plurality of fingers. A gas turbine engine includes a combustor section, a turbine section, and an annular finger seal. The annular finger seal includes a plurality of fingers and the annular finger seal is disposed at an adjoining interface between the combustor section and the turbine section. The annular finger seal may be mounted to the turbine section and may engage a radially inward facing surface, relative to the engine central longitudinal axis, of the combustor section.

Combustor finger seal

A first case includes a first plurality of threads, a second case includes a second plurality of threads, an interface provides at least one of anti-rotation or alignment with respect to the first case and the second case, and a nut includes a third plurality of threads configured to engage with the first plurality of threads and a fourth plurality of threads configured to engage with the second plurality of threads.

Turbine case coupling

A turbine exhaust case comprises a frame, a fairing, a heat shield and a mechanical linkage. The frame comprises an outer ring, an inner ring, and a plurality of struts joining the outer ring and the inner ring. The fairing comprising a ring-strut-ring structure disposed within the frame. The heat shield is disposed between the frame and the fairing. The mechanical linkage couples the heat shield to the fairing. In one embodiment, the heat shield comprises a multi-piece heat shield that inhibits heat transfer between the frame and the fairing. In various embodiments, the mechanical linkage comprises a slip joint or a fixed joint for coupling the heat shield to the fairing.

Mechanical linkage for segmented heat shield

A fairing sub-assemblyfor a turbine frame comprises an inner ring, an outer ringand a plurality of strut-shells. The inner ring is formed of a plurality of inner segments. The outer ring is formed of a plurality of outer segments. The plurality of strut-shellsconnecting the inner ringand the outer ring. In another embodiment, the fairing sub-assembly comprises an inner bandjoining the plurality of inner segmentsand the plurality of strut-shellsto form outer slots, and an outer bandjoining the plurality of outer segmentsand the plurality of strut-shellsto form inner slots. A method of assembling a fairingcomprises inserting the aforementioned fairing sub-assemblyinto an aft end of a turbine frame, inserting a plurality of forward strut-shellsinto the outer and inner slots at a forward end of the turbine frame, and joining the forward strut-shellsto the fairing sub-assembly

Bench aft sub-assembly for turbine exhaust case fairing

A turbine exhaust case frame () comprises an inner ring (), an outer ring (), and a plurality of load-bearing struts (). The inner ring is configured to carry load from inner bearings. The outer ring features a multi-function boss () with a service line aperture () and a mounting point for the turbine exhaust case. The load-bearing struts connect the inner ring to the outer ring, and have a service line passage () extending from the service line aperture to the inner ring.

Multi-function boss for a turbine exhaust case

A turbine exhaust case () comprises a fairing () defining an airflow path through the turbine exhaust case, and a multi-piece frame (). The multi-piece frame is disposed through and around the fairing to support a bearing load, and comprises an inner ring (), an outer ring () disposed concentrically outward of the inner ring, a plurality of bossed covers (), and a plurality of radial struts (). The plurality of bossed covers are bolted to the outer ring at locations circumferentially distributed about the outer diameter of the outer ring. The plurality of radial struts pass through the fairing and are secured via non-radial connectors () to the inner ring and the bossed covers.

Turbine exhaust case multi-piece framed

An assembly for a gas turbine engine includes a first casing, a fairing, and a multi-piece heat shield assembly. The fairing is disposed adjacent the first casing. The multi-piece heat shield assembly includes a first shield mounted to the first casing and extending between the first casing and the fairing, and a second shield mounted to the fairing and extending between the fairing and the first casing.

A frame employed in a turbine exhaust case of a gas turbine engine includes a frame outer ring, a frame inner ring, and a plurality of frame struts that connect the frame outer ring to the frame inner ring. The frame outer ring includes a plurality of bosses disposed circumferentially around the frame outer ring, wherein at least one of the plurality of bosses includes a mounting surface that receives and secures a removable bracket to the frame outer ring that supports a weight of the frame.

Multi-purpose mounting

A fairing () comprises an inner platform (), an outer platform (), a plurality of vane bodies (), and a flange (). The inner and outer rings define radially inner and outer boundaries of an airflow path. The vane bodies extend radially from the inner platform to the outer platform. The flange extends radially outward from the outer platform, and is defined by a frustoconical surface (S) extending radially inward and axially aft from a substantially radial upstream surface.

Angled cut to direct radiative heat load

A module for a gas turbine engine comprises a frame and a frame cooling system. The frame includes a circumferentially distributed plurality of radially extending struts. Each strut is joined to an outer frame section at an outer frame junction, and joined to an inner frame section at an inner frame junction. The frame cooling system comprises an inlet, a plurality of cooling air passages extending from the inlet radially through each of the plurality of frame struts; and an outlet. The outlet is in fluid communication with at least one of the cooling air passages and includes a film cooling hole formed through the frame proximate the outer frame junction.

Frame junction cooling holes

An assembly for a gas turbine engine includes a first module, a second module interconnected with the first module, a first gas turbine component, and a seal assembly. The first gas turbine component includes a body extending generally radially between an inner mounting portion and an outer seal carrier portion. The inner mounting portion is fastened to the first module such that the first gas turbine component forms a boundary between a first annular cavity in the first module, and a second annular cavity in the second module. The seal assembly is mounted to the seal carrier portion of the first gas turbine component, and includes a flow diverter assembly having a flow diverter and a finger seal commonly fastened to a first axial side of the seal carrier portion.

Seal support disk and assembly

A gas turbine engine assembly includes a first module, a second module rotatable about a center line of the gas turbine engine and fluidly coupled with the first module, and a multi-purpose seal support. The multi-purpose seal support includes an aft end secured to the first module, and a forward end disposed proximate the second module. The forward end has a discourager portion, a seal portion, and a meshing portion.

Growing community of inventors

Southington, CT, United States of America

Jonathan Ariel Scott