United Technologies Corporation

Raytheon Technologies Corporation

Rtx Corporation

Christopher J Peters

Dominic J Mongillo, Jr

Raymond C Surace

Timothy J Jennings

Jeffrey J DeGray

Emma J Place

Jeremy B Fredette

Conway Chuong

Joey Wong

Ross Wilson

Alex J Simpson

Zachary D Ryan

Jose R Paulino

Kang Chang Yeh

Hung Liang Chou

Shelton O Duelm

Dave J Hyland

Mark S Hunter

Daniel R Bowers

Dominic J Mongillo

Jeffrey J Degray

Jeffrey J Degraym

Daniel J Geddes

A casting core assembly for a gas turbine engine component according to an implementation includes a skin core corresponding to a first cooling passage of an airfoil. The first cooling passage includes a first section and a tip flag section joined at a first bend. The skin core includes a first portion corresponding to the first section and a tip flag portion corresponding to the tip flag section. The skin core includes at least one arcuate slot corresponding to at least one turning vane of the airfoil. A method of forming an airfoil for a gas turbine engine is also disclosed.

Cooling arrangement for gas turbine engine component

An airfoil for a gas turbine engine according to an example of the present disclosure includes an airfoil section extending in a radial direction from a root section to a tip portion. The airfoil section has an external wall and an internal wall. The airfoil section establishes an internal cooling arrangement including a first cooling passage having a first section and a tip flag section. The tip flag section extends in the chordwise direction along the tip portion from the first section. The first section includes a plurality of branched paths established by at least one turning vane.

An airfoil core includes a first core portion that has a hybrid skin core, a tip flag core, and a trailing edge core. A second core portion has a serpentine core and a leading edge core.

Multi-walled airfoil core

Aspects of the disclosure are directed to a seal comprising: a shoe, and at least two beams coupled to the shoe, where a first width associated with the beams exceeds a second width associated with the shoe in a reference direction. Aspects of the disclosure are directed to an engine comprising: a compressor section, a turbine section, and a floating, non-contact seal that includes: a shoe, and at least two beams coupled to the shoe, where the beams extend past an edge of a flowpath surface associated with the shoe in a reference direction.

Floating, non-contact seal and dimensions thereof

A method of forming an airfoil, includes forming a hybrid skin core, a tip flag core, and a trailing edge core. The hybrid skin core, tip flag core, and trailing edge core are connected to form a first core portion. A leading edge core and a serpentine core are formed. The first core portion, the leading edge core, and the serpentine core are assembled together to form an airfoil core. An airfoil is formed around the airfoil core.

A non-contact seal assembly includes a plurality of seal shoes, a seal base and a plurality of spring elements. A first of the spring elements includes a first mount, a second mount and a spring beam. The spring beam extends a length longitudinally along a centerline from the first mount to the second mount. The spring beam includes opposing first and second surfaces. The first surface is disposed a first distance from the centerline, and the second surface is disposed a second distance from the centerline. The first distance and the second distance change as the spring beam extends longitudinally along the centerline to provide at least a portion of the spring beam with a tapered geometry. The portion of the spring beam has a longitudinal length that is at least about five percent of the length of the spring beam.

Shaped spring element for a non-contact seal device

Aspects of the disclosure are directed to a floating, non-contact seal comprising: a shoe, and at least three beams, each beam having a first axial end and a second axial end, where the first axial ends are coupled to the shoe and the second axial ends are coupled to a ring structure. Aspects of the disclosure are directed to an engine comprising: a first structure, a second structure configured to rotate relative to the first structure, and a floating, non-contact seal that interfaces the first structure and the second structure, where the seal includes: a shoe, and at least three beams, where each beam has a first axial end and a second axial end, where the first axial ends are coupled to the shoe and the second axial ends are coupled to a ring structure.

Floating, non-contact seal with at least three beams

A seal assembly includes an annular base, a spring, a shoe, a first channel, a seal cover, and a seal. The spring includes a beam and is connected to the annular base. The shoe is disposed radially inward of the annular base and connected to the spring. The shoe includes an upstream portion, a downstream portion, and a lip connected to and extending radially outward from the upstream portion of the shoe. The spring extends from the annular base to the shoe. The first channel is positioned between the shoe and the beam of the spring. The seal is disposed between the seal cover and the shoe such that a downstream face of the seal is in contact with an upstream face of the shoe.

Floating non-contact seal vertical lip

An assembly is provided for rotational equipment with an axial centerline. This assembly includes a primary seal device, a ring structure and a secondary seal device. The primary seal device is configured as a hydrostatic non-contact seal device. The primary seal device includes a plurality of seal shoes and a seal base. The seal shoes are arranged circumferentially about the axial centerline in an annular array. The seal base circumscribes the annular array of the seal shoes. The ring structure is axially engaged with the seal base. The secondary seal device is mounted with the ring structure. The secondary seal device includes a seal ring body and an alignment tab. The seal ring body is configured to substantially seal an annular gap between the ring structure and the seal base. The alignment tab projects out from the seal ring body and into an aperture in the ring structure. The alignment tab is adapted to substantially rotationally locate and/or fix the secondary seal device to the ring structure.

Secondary seal device(s) with alignment tab(s)

A non-contact seal assembly is provided. This assembly includes a plurality of seal shoes, a seal base and a plurality of spring elements. The seal shoes are arranged about a centerline in an annular array. The seal shoes include a first seal shoe extending axially along the centerline between a first shoe end and a second shoe end. An aperture may extend partially axially into the first seal shoe from the first shoe end and laterally within the first seal shoe. The seal base circumscribes the annular array of the seal shoes. Each of the spring elements is radially between and connects a respective one of the seal shoes with the seal base.

Seal shoe for a hydrostatic non-contact seal device

A seal assembly for an exhaust duct section of a gas turbine engine includes a multiple of springs that axially extend from a split hoop opposite a seal surface.

Growing community of inventors

West Hartford, CT, United States of America

Christopher J Peters