Abstract: This invention relates to a method of thermally isolating a bearing located near the combustion region in a gas turbine. Air is bled from an intermediate stage of the compressor turbine and is arranged to be fed to the central pipe of a coaxial piping arrangement which leads to the bearing housing. The housing for the bearing is arranged to have cooling air passages located therein to allow the air to circulate around and thus isolate the various parts of the bearing from the hot ambient. The air which has thereby acquired heat is subsequently lead back to the coaxial piping arrangement and is fed outwardly through the turbine in the space between the outer pipe and the central pipe.

Abstract: This invention relates to a device which is capable of accurately transferring a rotating movement from a master control to a pivotal vane tip in a gas turbine engine. A series of stationary vanes which are housed inside the casing of a gas turbine are each provided with a trailing rotatable vane tip. The device to which this application is directed is mounted on the casing of the gas turbine in a sealed manner and is connected to the rotatable vane tip. The vane tip is continuously biased in a radially outward direction by the motion transfer device to assure the best possible seal of the vane tip in the turbine. Provision is made to allow the vane tip to have some radial flexibility to prevent binding of the vane tip under thermal cycling stresses.

Abstract: This invention relates to a method of moving a set of adjustable trailing vanes in a gas turbine engine of the "split-shaft" type. The vanes are moved by an adjusting ring which is made to completely encircle the casing of the turbine and connect to each vane by means of a rotator assembly. Provision is made to allow for connection of the turbine casing so that the binding or flexing of the adjustor ring assembly during thermal cycling is avoided. A series of pitman arms are pivotally interconnected between the adjustor ring assembly and each vane rotator assembly. The vane rotator assembly is provided to intercouple the adjustor ring assembly to each pivoting vane while at the same time providing some radial flexibility for the vane itself to prevent binding of the blade and actuator during thermal cycling. Provision is also made to bias each pivoting vane in the particular direction in the turbine during the operation of the turbine.

Abstract: This invention relates to a vane assembly for a split-shaft gas turbine engine. The invention relates to a vane assembly which is placed in the hot gas stream to control diffusion and to deflect the hot gas just prior to passage through the blades of the power wheel. The vane assembly is characterized by having each controlling and deflecting blade constructed in two cooperating parts, a forward portion of the vane which is hollow and stationary to control diffusion and a trailing portion which is allowed to pivot through a small angle to control deflection. The vane assembly is constructed in sections to have two complete vanes per section and the sections are fitted into circumferential slots in the casing of the turbine. The vane tip actuators are passed through the turbine casing and are fitted to the trailing portions of each vane so that the trailing portions of the entire assembly move as a unit by a single control mechanism.

Abstract: This invention relates to cooling a section of a split shaft gas turbine engine. Because combustion takes place in the region of the shaft-split, overheating may occur and care must be taken to ensure that this portion of the turbine is sufficiently cooled. This invention is concerned with bleeding a portion of the compressed air from an intermediate stage of the compressor turbine and feeding the compressed air into a manifold. Next the air is fed by means of suitable conduit members into the split-shaft region of the turbine. Provision is made to feed this air to the faces of the power disc for the compressor section and the face of the power disc for the output power section of the turbine. Various other parts of the turbine are also cooled in the split shaft region of the turbine.