Provided is a center vent tube support device that can prevent transmission of abnormal load between members and prevent abrasion of a contact surface. A device includes: an annular sleeve having an inner surface that comes into contact with an outer surface of a center vent tube; a ring formed of a pair of segments and placed between the sleeve and a main shaft; and an annular nut for fixing the ring to the sleeve. An outer surface of the sleeve or the nut includes a pressurizing surface formed as a conical surface. Each of the ring segments includes a supporting surface formed as a cylindrical surface having a diameter equal to an inner diameter of the main shaft in a portion where the device is to be installed, a bearing surface formed as a conical surface having a vertex angle equal to that of the conical surface forming the pressurizing surface, a pair of side surfaces, and a pair of end faces formed as planes each spaced from a plane including the axis. The supporting surface and the bearing surface are formed of an outer surface of a rim portion of the ring segment and an inner surface of a bore portion of the ring segment, respectively. A diameter of a circle circumscribing a projected shape of the device in a direction perpendicular to the end face is smaller than an inner diameter of a smallest-diameter portion of the main shaft.

A segment seal is configured to seal an annular clearance between a housing and a rotary shaft in a state in which a pair of seal rings are attached in an unrotatable state between one end portion of the housing and a support member attached to the housing so as to be opposite to the one end portion in an axial direction. The segment seal includes an anti-rotation member placed not to rotate relative to the housing or the support member, provided with a pair of raised portions fitted to the pair of seal rings to prevent rotation of the pair of seal rings, and configured such that at least one of the raised portions has a shape fittable only to either one of the seal rings.

Embodiments of the disclosure provide a tool and method for alignment adjustment of machinery. The tool may include a bottom plate, a top plate oriented in parallel planes, a low friction intermediate element between bottom plate and top plate, and a hydraulic actuator or electro-mechanic actuator arranged between the bottom plate and the top plate and capable of moving the top plate relative to the bottom plate.

Fixing set for securely assembling and locking a blade shaped element, for instance a turbine blade, on a support, for instance a turbine rotor. The blade shaped element is adapted to be inserted into a groove of the external surface of the support and the fixing set includes first, second and third locking elements adapted to be inserted into the groove, between the lower end surface of the root portion of the blade shaped element and the groove base surface. The first, second and third locking elements are adapted to securely lock the blade shaped element on the support and are further adapted to allow easy and simple installation by an operator with no need of additional working and extra machining.

A control ring for a stage of variable-pitch vanes for a turbine engine includes at least one member for bearing on a casing and means for fixing the member. The member includes a bushing with an axial bore for the passage of the member or an element for supporting the member. A through-slot opens into the bore and allows for substantial radial deformation of the bushing. The member further includes an outer thread for screwing the bushing into a complementary thread of a hole in the body, thereby deforming the bushing. The member or support can be mounted and moved inside the bore, to a second position, in which the bushing is radially constrained and is tightly mounted on the member or support, which is thus immobilized in relation to the bushing.

A turbine ring assembly includes ring sectors made of ceramic matrix composite material forming a turbine ring and a ring support structure having first and second annular flanges, each ring sector having first and second tabs held between the flanges. First and second holder elements secured to the first annular flange being received in first and second openings in the first tab, while first and second holder elements secured to the second annular flange are in first and second openings in the second tab. Radial clearance is being present when cold between the openings and the portions of the holder elements present in the openings. The first and second annular flanges include, on their faces facing the first and second tabs, a plurality of thrust portions distributed in circumferential manner over the flanges, the ends of the tabs, when cold, being in radial abutment against two thrust portions.

A gas turbine engine assembly includes a turbine shroud having a carrier segment and adjacent blade track segments. The carrier segment is arranged around a central axis of the gas turbine engine and the blade track segments are supported by the carrier segment. The turbine shroud segment further includes a retainer that is configured to locate the blade track segments radially relative to the central axis of the gas turbine engine.

A flow metering and retention system includes a first disk that is annular in shape surrounding a centerline and extending axially along the centerline, a first coverplate axially rearward of the first disk with the first coverplate having an axially rearward extending arm, a second disk that is annular in shape surrounding the centerline and rearward of the first coverplate, a second coverplate at least partially between the first coverplate and the second disk; and a ring adjacent to the radially outer side of the slot of the second disk. The second disk has a slot into which the arm of the first coverplate extends with the slot having a radially outer side and a radially inner side, and the ring is configured to meter air flowing between the radially outer side of the slot and the arm of the first coverplate.

An assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a first annular case that has a first body extending from a first end portion and a second annular case that has a second body extending along a longitudinal axis from a second end portion. The first end portion has a first flange. The first flange has at least one mounting assembly. The at least one mounting assembly has a first aperture dimensioned to receive a fastener and a first ramped surface that extends axially from the first aperture. The second end portion includes at least one flange that defines a receptacle dimensioned to receive the first end portion and a second aperture dimensioned to receive the fastener and a second ramped surface. The first annular case is moveable in an axial direction relative to the longitudinal axis through an axial opening of the receptacle such that the first end portion is received in the receptacle, and is rotatable about the longitudinal axis to define an interface between the first and second ramped surfaces to interlock the first end portion in the receptacle and limit movement of the first annular case relative to the longitudinal axis. A method of assembly for a gas turbine engine is also disclosed.

A compression rod engagement apparatus is provided that includes an engagement feature, an engagement feature pin, and a mounting member. The engagement feature is attached to the engagement feature pin. The engagement feature pin is engaged with the mounting member in a home position and axial travel of the engagement feature pin along a lengthwise axis away from the home position in either axial direction is resisted by at least one spring force.