Abstract: 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.

Abstract: An assembly for rotational equipment includes a plurality of seal shoes, a seal base, a plurality of spring elements and a frangible element. The seal shoes are arranged around an axis in an annular array. 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 and the seal base. A first of the spring elements includes a first mount, a second mount and a spring beam. The first mount is connected to a first of the seal shoes. The second mount is connected to the seal base. The spring beam extends longitudinally between and connects the first mount and the second mount. The frangible element is configured to restrict radial outward movement of the first of the seal shoes.

Abstract: A turbine engine includes a diffuser connecting a compressor section and a turbine section. The diffuser includes a diffuser frame and multiple diffuser case sections are connected to the diffuser frame.

Abstract: An assembly for rotational equipment includes a plurality of seal shoes, a seal base, a plurality of spring elements and a frangible element. The seal shoes are arranged around an axis in an annular array. 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 and the seal base. A first of the spring elements includes a first mount, a second mount and a spring beam. The first mount is connected to a first of the seal shoes. The second mount is connected to the seal base. The spring beam extends longitudinally between and connects the first mount and the second mount. The frangible element is configured to restrict radial outward movement of the first of the seal shoes.

Abstract: 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.

Abstract: Aspects of the disclosure are directed to a floating, non-contact seal comprising: a shoe, a first beam coupled to the shoe, and a second beam coupled to the shoe, where the first beam is oriented at a first angle with respect to the shoe, the first angle having a first value that is greater than five degrees. 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, a first beam coupled to the shoe, and a second beam coupled to the shoe, where the first beam is oriented at a first angle with respect to the shoe, the first angle having a first value that is greater than five degrees.

Abstract: 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.

Abstract: 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.

Abstract: A hydrostatic seal assembly for a gas turbine engine includes a shoe movable radially relative to a longitudinal engine axis. At least one beam supports radial movement of the shoe. A secondary seal is fixed relative to the shoe. A rail is attached to the shoe and in sealing engagement with the secondary seal. A gas turbine engine and a method of creating a seal with a hydrostatic seal are also disclosed.

Abstract: 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, a first beam coupled to the shoe, and a second beam coupled to the shoe, where during a non-operational state of the engine a reference point of the shoe is substantially centered within a range of radial deflections of the reference point of the shoe over the operating range of the engine.

Abstract: An apparatus for sealing a circumferential gap between a stationary component and a rotating member is disclosed. The rotating member is configured to rotate about a longitudinal axis and has a radially outer surface disposed at a first non-zero angle with respect to the longitudinal axis. The apparatus includes a stator disposed circumferentially about the longitudinal axis and a shoe configured for translation in a radial direction with respect to the stator. The shoe includes a circumferential surface and a plurality of protrusions extending radially inward from the circumferential surface toward the rotating member, each one of the plurality of protrusions having a length configured to maintain a clearance gap with respect to the rotating member.

Abstract: A seal according to the present disclosure includes a plate, and a floating shoe supported with respect to the plate in a first direction. The floating shoe has a sealing feature extending in a second direction perpendicular to the first direction. At least one bearing is between the plate and the floating shoe. The bearing is configured to facilitate movement of the floating shoe with respect to the plate in the second direction. A gas turbine engine including the seal and a method of sealing a rotating component with respect to a stationary component are also disclosed.

Abstract: A stator vane arrangement for a turbine engine includes a first vane platform, a second vane platform and a plurality of stator vanes extending radially between the first and the second vane platforms. The first and the second vane platforms extend circumferentially around an axis, and the first vane platform includes an aperture. The stator vanes are arranged circumferentially around the axis, and include a first stator vane that extends radially into the aperture and is fastened to the first vane platform.

Abstract: A gas turbine engine includes an engine static structure. A fairing is supported relative to the engine static structure and configured to provide a flow path surface of a flow path extending in an axial direction. A seal plate has first and second ends radially spaced from one another with respect to the axial direction. The first end is operatively secured to the engine static structure. The second end is configured to seal relative to the fairing. The seal plate includes a portion between the first and second ends that extends substantially in the axial direction and configured to permit the second end to move away from the fairing in the axial direction relative to the first end in response to thermal growth.

Abstract: A fairing sub-assembly 88 for a turbine frame comprises an inner ring 50, an outer ring 48 and a plurality of strut-shells. The inner ring is formed of a plurality of inner segments 82. The outer ring is formed of a plurality of outer segments 80. The plurality of strut-shells 84, 86 connecting the inner ring 48 and the outer ring 50. In another embodiment, the fairing sub-assembly comprises an inner band 45 joining the plurality of inner segments 82 and the plurality of strut-shells 86 to form outer slots, and an outer band 44 joining the plurality of outer segments 80 and the plurality of strut-shells 86 to form inner slots. A method of assembling a fairing 46 comprises inserting the aforementioned fairing sub-assembly 38 into an aft end of a turbine frame 42, inserting a plurality of forward strut-shells 84 into the outer and inner slots at a forward end of the turbine frame 42, and joining the forward strut-shells 84 to the fairing sub-assembly 88.

Abstract: A seal plate for a gas turbine engine includes an annular wall provided about an axis and extending between first and second ends that are radially spaced from one another with respect to the axis. The first end includes an axially extending pilot. The second end includes an axially extending flange and an adjacent annular seal seat. The wall includes a portion between the first and second ends that extend substantially in the axial direction and is configured to permit the second end to move axially relative to the first end in response to thermal growth.

Abstract: 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.

Abstract: A seal assembly includes first and second rings. The first ring includes a first outer ring, a first beam connected to the first outer ring, and a first shoe. The first shoe includes free and fixed ends and is configured to move radially. The second seal ring is disposed axially adjacent and is attached to the first seal ring. The second seal ring includes a second outer ring, a second beam connected to the second outer ring, and a second shoe. The second shoe includes free and fixed ends and is configured to move in a generally radial direction. The free end of the second shoe is disposed axially adjacent to the fixed end of the first shoe. The fixed end of the second shoe is disposed axially adjacent to the free end of the first shoe.

Abstract: A seal system for a gas turbine engine is disclosed. The seal system includes a fairing. The seal system also includes a finger seal retention unit attached to the fairing, the finger seal retention unit comprising a channel defining an opening between the fairing and the finger seal retention unit. The seal system also includes a finger seal comprising a tab corresponding to the channel of the finger seal retention unit, the finger seal configured to be removably attached to the finger seal retention unit by inserting the tab into the channel.

Abstract: A seal assembly includes a side ring and a cartridge. The side ring comprises an annular piece of solid material. The cartridge is affixed to the side ring and comprises a shoulder, a beam connected to and extending from the shoulder, a shoe attached to an end of the beam, and a rotary seal disposed on a bottom portion of the shoe.