Abstract: A magnetic seal system adapted for use between a support structure and a rotatable shaft. The seal system includes a rotating annular seal assembly surrounding the shaft and rotating therewith, which includes an annular seal, and a non-rotating biasing assembly sealingly mounted to the support structure around the shaft and axially engaging the annular seal assembly. The biasing assembly includes an annular magnet unit axially displaceable relative to the shaft and supported surrounding the shaft. The annular magnet unit exerting an attracting force on the annular seal assembly to biasingly displace the annular magnet unit towards the annular seal. A bias member unit is also provided for non-magnetically biasing the annular magnet unit axially relative to the shaft towards the annular seal. Adjacent contacting surfaces between the annular seal and the annular magnet unit biasingly contact one another to form a sealing interface therebetween.

Abstract: A contacting face seal component comprises a circumferential body defined as an annulus extending between an outer periphery and an inner periphery around a center axis, the circumferential body including a contact surface configured for face-sealing engagement with a relatively rotating member, an annular groove defined in the contact surface about the center axis, the annular groove defining in the contact face a sealing lip and at least one load distribution pad radially spaced from one another by the annular groove; and at least one passage extending between the annular groove and the outer periphery to fluidly connect with an outer side of the circumferential body.

Abstract: A magnetic seal system adapted for use between a support structure and a rotatable shaft. The seal system includes a rotating annular seal assembly surrounding the shaft and rotating therewith, which includes an annular seal, and a non-rotating biasing assembly sealingly mounted to the support structure around the shaft and axially engaging the annular seal assembly. The biasing assembly includes an annular magnet unit axially displaceable relative to the shaft and supported surrounding the shaft. The annular magnet unit exerting an attracting force on the annular seal assembly to biasingly displace the annular magnet unit towards the annular seal. A bias member unit is also provided for non-magnetically biasing the annular magnet unit axially relative to the shaft towards the annular seal. Adjacent contacting surfaces between the annular seal and the annular magnet unit biasingly contact one another to form a sealing interface therebetween.

Abstract: A carbon seal assembly comprises an annular seal runner adapted to be sealingly mounted to a shaft to rotate therewith. An annular member is secured to a structure, the annular member having an annular body and a projection extending from the body toward the seal runner in an axial direction relative to an axis of the runner. A axial gap is defined between the member and the seal runner when secured to the shaft and structure respectively, with the projecting extending into only a portion of the gap, such that the gap defines a first width portion and a second width portion, with the member and the seal runner being made of complementary materials for magnetic attraction therebetween. An annular carbon element is mounted to the seal runner to rotate therewith and positioned in the first width portion of the gap, the carbon element having an annular wear surface abutting against the annular member, a plane of the annular wear surface being axially offset from the second width portion of the gap.

Abstract: A carbon seal assembly comprises an annular seal runner adapted to be sealingly mounted to a shaft to rotate therewith. An annular member is secured to a structure, the annular member having an annular body and a projection extending from the body toward the seal runner in an axial direction relative to an axis of the runner. A axial gap is defined between the member and the seal runner when secured to the shaft and structure respectively, with the projecting extending into only a portion of the gap, such that the gap defines a first width portion and a second width portion, with the member and the seal runner being made of complementary materials for magnetic attraction therebetween. An annular carbon element is mounted to the seal runner to rotate therewith and positioned in the first width portion of the gap, the carbon element having an annular wear surface abutting against the annular member, a plane of the annular wear surface being axially offset from the second width portion of the gap.

Abstract: A gas turbine engine airfoil has a platform cooling scheme including an impingement hole for directing cooling air against an undersurface of the airfoil platform.

Abstract: A ring seal for sealing an annular gap defined between opposed surfaces of concentric inner and outer annular engine parts in a gas turbine engine. The ring seal being wholly disposed within the annular gap and having a wave pattern with alternating peaks. The ring seal radially inwardly loads the inner engine part and provides a fluid seal between the inner and outer engine parts.

Abstract: A gas turbine engine airfoil has a platform cooling scheme including an impingement hole for directing cooling air against an undersurface of the airfoil platform.

Abstract: A ring seal for sealing an annular gap defined between opposed surfaces of concentric inner and outer annular engine parts in a gas turbine engine. The ring seal being wholly disposed within the annular gap and having a wave pattern with alternating peaks. The ring seal radially inwardly loads the inner engine part and provides a fluid seal between the inner and outer engine parts.

Abstract: An assembly for a gas turbine engine, the assembly comprising a combustor and a vane assembly downstream from the combustor. The vane assembly includes at least one airfoil radially extending between an inner and outer platform defining an annular gas path therebetween. At least the outer platform forms a first sliding joint connection with an adjacent outer combustor wall such that radial sealing between the outer platform and the outer combustor wall is provided at engine operating temperature, while permitting relative axial displacement therebetween.

Abstract: A blade for mounting in an annular array about a rotary hub, the blade having: a blade root; an airfoil profile with a concave pressure side surface; a chord line extending between a leading edge and a trailing edge; and a blade tip, where the blade has a recess in the pressure side surface with an outer periphery disposed radially inwardly from the blade tip, and inwardly along the chord line from the leading edge and from the trailing edge.

Abstract: An assembly for a gas turbine engine, the assembly comprising a combustor and a vane assembly downstream from the combustor. The vane assembly includes at least one airfoil radially extending between an inner and outer platform defining an annular gas path therebetween. At least the outer platform forms a first sliding joint connection with an adjacent outer combustor wall such that radial sealing between the outer platform and the outer combustor wall is provided at engine operating temperature, while permitting relative axial displacement therebetween.

Abstract: A blade for mounting in an annular array about a rotary hub, the blade having: a blade root; an airfoil profile with a concave pressure side surface; a chord line extending between a leading edge and a trailing edge; and a blade tip, where the blade has a recess in the pressure side surface with an outer periphery disposed radially inwardly from the blade tip, and inwardly along the chord line from the leading edge and from the trailing edge.