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公开(公告)号：US20180283398A1
公开(公告)日：2018-10-04
申请号：US15478899
申请日：2017-04-04
摘要： A bellcrank assembly for variable vane assembly of a gas turbine engine includes a first bellcrank segment. Also included is a second bellcrank segment. Further included is a bolt extending through respective interior barrels defined by the first and second bellcrank segments to couple the first and second bellcrank segments to each other. Yet further included is a torque frame wall defining an aperture, the bolt extending through the aperture.
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公开(公告)号：US11242761B2
公开(公告)日：2022-02-08
申请号：US16793307
申请日：2020-02-18
摘要： A rotor disk assembly for a gas turbine engine includes a rotor disk that defines an axis, the rotor disk comprising a slot within a rim of the disk and a spacer within the slot, the spacer having a clearance feature sized to permit rotation of a rotor blade from an insertion position to an installed position.
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公开(公告)号：US10815820B2
公开(公告)日：2020-10-27
申请号：US16267581
申请日：2019-02-05
发明人： William S. Pratt , Ryan M. Stanley , Adam Hart
摘要： A synchronizing assembly including: a synchronizing ring having a countersunk orifice; and a bumper assembly comprising: a bumper at least partially enclosing a cavity, the bumper comprising an outward side, an inward side opposite the outward side, a first side extending between the outward side and the inward side, a first opening on the outward side extending into the bumper to define a first portion of the cavity; and a second opening on the first side extending into the bumper to define a second portion of the cavity; and a bolt comprising a bolt head and a bolt shank, wherein the bolt shank extends through the first opening and the bolt head is secured within the second portion of the cavity, wherein the bumper further comprises a raised boss extending away from the outward surface, the raised boss configured to mate with the countersunk orifice of the synchronizing ring.
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公开(公告)号：US20200325792A1
公开(公告)日：2020-10-15
申请号：US16379179
申请日：2019-04-09
发明人： William S. Pratt , Matthew E. Bintz
摘要： A vane arm assembly for a gas turbine engine includes a vane stem having a circumferential groove axially spaced from an outer end of the vane stem. The assembly also includes a vane arm defining an arm aperture that the vane stem is disposed within. The assembly further includes a mechanical fastener retaining an axial position of the vane arm in the axial direction. The assembly yet further includes a retention clip having a base portion and at least one clip arm, the base portion defining a clip aperture that the vane stem is disposed within, the base portion disposed within the circumferential groove of the vane stem to couple the retention clip to the vane stem, the at least one clip arm including a retention member engaged with the vane arm to provide redundant axial retention of the vane arm.
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公开(公告)号：US10526911B2
公开(公告)日：2020-01-07
申请号：US15630650
申请日：2017-06-22
摘要： A synchronization ring for a variable vane assembly of a gas turbine engine may include a first ring portion and a second ring portion. The first ring portion and the second ring portion may be detachably coupled together to jointly define a plurality of cylindrical bores circumferentially distributed around the synchronization ring and extending radially through the synchronization ring.
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公开(公告)号：US20210222580A1
公开(公告)日：2021-07-22
申请号：US16747065
申请日：2020-01-20
摘要： A rotor stack for a gas turbine engine includes a first rotor disk with a first rotor spacer arm, the first rotor spacer arm having a first flange with an outboard flange surface and an inboard flange surface, a first hole along an axis through the first flange, the first hole having a counterbore in the outboard flange surface; a second rotor disk with a web having a second hole along the axis; a third rotor disk with a third rotor spacer arm, the third rotor spacer arm having a third flange with an outboard flange surface and an inboard flange surface, a third hole along the axis through the third flange, the third hole having a counterbore in the inboard flange surface; and a bushing with a tubular body and a flange that extends therefrom, the tubular body comprising at least one axial groove along an outer diameter thereof, the bushing extends through the first hole, the second hole and partially into the counterbore in the inboard flange surface of the third hole.
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公开(公告)号：US20200232336A1
公开(公告)日：2020-07-23
申请号：US16251674
申请日：2019-01-18
摘要： A vane arm assembly for a gas turbine engine is provided including: a vane arm having a first end, a second end opposite the first end, and an aperture proximate the second end, the aperture being defined by an aperture wall; a vane stem extending through the aperture of the vane arm; a mechanical fastener retaining a position of the vane arm in the longitudinal direction of the vane stem; and an impedance clip partially enclosing a portion of the second end of the vane arm to provide redundant position retention of the vane arm in the longitudinal direction of the vane stem.
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公开(公告)号：US10590795B2
公开(公告)日：2020-03-17
申请号：US15786367
申请日：2017-10-17
发明人： William S. Pratt , Anand Nagaraj , Diane C. Kjelby
摘要： A vane arm may comprise a first end having a first surface and a second surface opposite the first surface. A vane stem aperture may be formed through the first end of the vane arm. The first surface may define a first perimeter of the vane stem aperture. The second surface may defines a second perimeter of the vane stem aperture. The second perimeter may comprise a circular or elliptical shape. A first wedge face and second wedge face may define a portion of the vane stem aperture.
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公开(公告)号：US20190338665A1
公开(公告)日：2019-11-07
申请号：US15968058
申请日：2018-05-01
IPC分类号： F01D17/16
摘要： A variable vane actuation system of a gas turbine engine is provided. The variable vane actuation system including: a variable vane; a vane stem operably associated with the variable vane, wherein the variable vane is configured to rotate with the vane stem; a vane arm having vane stem end and a vane pin end opposite the vane stem end, the vane arm being operably connected to the vane stem at the vane stem end; and a rotational variable differential transformer operably connected to the vane stem, the rotational variable differential transformer configured to detect an amount of rotation of the vane stem.
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公开(公告)号：US20190264574A1
公开(公告)日：2019-08-29
申请号：US15908268
申请日：2018-02-28
摘要： A vane arm assembly for a gas turbine engine. The vane arm assembly includes a vane arm defining an aperture at an end thereof with an aperture wall. The vane arm assembly also includes a vane stem extending through the aperture of the vane arm. The vane arm assembly further includes a mechanical fastener retaining a position of the vane arm in the longitudinal direction of the vane stem. The vane arm assembly yet further includes an impedance ring disposed within the aperture of the vane arm and within an impedance ring groove defined by the vane stem to provide redundant position retention of the vane arm in the longitudinal direction of the vane stem.
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