A turbine support assembly includes a turbine rotor joined to a fan shaft through a support shaft. The support shaft is joined to the fan shaft in a V-configuration having first and second legs joined together at an apex and inclined axially apart, with at least the first leg forming an integral part of the fan shaft. The second leg is rotatably supportable to a frame. The V-configuration increases the stiffness of the turbine support to reduce blade tip clearances. The present invention also provides an annular integral bolt heat shield and axial retention apparatus to axially retain bolts used for holding together two rotor elements during assembly when the bolts are otherwise subject to sliding into a closed cavity of the assembled engine or one of its modules. The integral retainer and heat shield engage the bolts disposed through bolt holes in a gas turbine engine rotor shaft so that the bolts remain straight during assembly when a second rotor element such as a second shaft is being attached to the first shaft, and bolt holes in the second shaft have to engage and fit over the bolts of the first shaft. One particular embodiment of the present invention provides a low pressure turbine rotor shaft assembly of a low pressure turbine module wherein forward and aft shafts are attached by bolts which have bolt heads in a closed cavity of the module and are slidably disposed through corresponding bolt holes of each shaft such that the bolt heads are disposed aft of the aft shaft. An integral heat shield and axial bolt retainer is mounted to the aft shaft aft of the bolt heads so as to trap and retain the bolt heads between the shield and the aft shaft.

Turbine support assembly including turbine heat shield and bolt retainer assembly

A rotor assembly for supporting rotor blades includes a plurality of axially adjoining discrete disks each having a rim. The rims include axial dovetail posts defining therebetween dovetail grooves for collectively supporting a respective blade dovetail therein. The disks are fixedly joined together by integral beams so that upon a crack failure of one of the disks, centrifugal load from the failed disk is transferred to an adjacent disk and crack propagation thereto is inhibited.

Burst resistant rotor disk assembly

A rotor assembly for supporting rotor blades includes a plurality of axially adjoining discrete disks each having a rim, web, and hub. The rims include axial dovetail grooves for collectively supporting a respective blade dovetail therein. Each of the disks includes at least one axially extending annular arm joined integrally with the disk and fixedly joined to an adjacent one of the arms. The disks are fixedly joined together solely by the blade dovetails in the rim dovetail grooves and by the arms so that upon a crack failure of one of the disks, centrifugal load from the failed disk is transferred to an adjacent disk.

Multiple rotor disk assembly

A flange (20) for connection between an axial compressor and high-pressure rotor disc unit (14) in a gas turbine (10), wherein the flange (20) has a body (22) with a frusto-conical shape which is joined to a shaft (12) of the axial compressor by means of a hub (24) which has a cylindrical shape and which, at the larger base of the frustum of the cone of the body (22) is connected to the rotor disc unit (14) by means of an extension (26) of the hub in the form of a circular ring, a circumferential recess (28) provided in a surface (29) of the extension (26) which faces the rotor disc unit (14) being connected by interference with a projection, which is complementary to the recess and is provided on the rotor disc unit (14); the body (22) has an outer generatrix which is inclined relative to the direction at right-angles to the axis (X) by an angle .alpha.1 of between 25° and 35° and an inner generatrix which is inclined by an angle .alpha.2 of between 12° and 18°.

Flange for connection between an axial compressor and high-pressure rotor disc unit in a gas turbine

The present invention provides apparatus and methods for balancing stacked components of rotating machinery, such as in a gas turbine engine. Unlike conventional processes and devices for balancing stacked components, the present invention may use a single non-parallel spacer for obtaining an acceptable and repeatable component group balance. The non-parallel spacer may be used to compensate for rotor bow and the associated imbalance of the rotor group. By indexing a spacer with non-parallel faces, situated terminally at the end of the stack adjacent to the nut, rotor balance can be achieved without disassembly of the rotor group and clocking of its individual components. A spacer may also be disposed at any one or more of the interfaces between various components in the stack.

Non-parallel spacer for improved rotor group balance

A lightweight, rotor assembly for a gas turbine engine having a critical speed characteristic well above the operating speed is disclosed. Various construction details which enhance the axial stiffness of the rotor assembly and which shield a portion of the disk from working medium gases are developed. The rotor assembly employs a frustoconical member to connect a shaft to the disk.

Rotor assembly having a multistage disk

Rotoranordnung mit mehrstufiger scheibe

L'ASSEMBLAGE DE ROTOR POUR TURBOMACHINE A UNE VITESSE CRITIQUE SITUEE BIEN AU-DESSUS DE LA VITESSE DE FONCTIONNEMENT DE L'ASSEMBLAGE DU ROTOR. LA CONSTRUCTION DU ROTOR AMELIORE LA RIGIDITE AXIALE DE L'ASSEMBLAGE DE ROTOR 18 ET COMPORTE UN MOYEN POUR PROTEGER UNE PARTIE DU DISQUE DE ROTOR 36 CONTRE LES GAZ DU MILIEU DE TRAVAIL. L'ASSEMBLAGE DE ROTOR A UN ELEMENT EN TRONC DE CONE 30 POUR RELIER LE DISQUE A L'ARBRE DE L'ASSEMBLAGE DE ROTOR.

Rowley Robert Lee

Papers

Rotor assembly having a multistage disk

Rotoranordnung mit mehrstufiger scheibe

Assemblage de rotor ayant un disque a plusieurs etages