Abstract: A gas turbine with at least one fixed guide vane ring (1) with a sealing ring (3) cooperating with a sealing member on the turbine rotor (7). The sealing ring (3) is connected to the guide vane ring (1) through a number of links (19) which are suitably oriented in a substantially tangential direction. The attachment of the sealing ring (3) by means of the links (19) means a perfect centering of the sealing ring (3) relative to the rotor (7) when the guide vane ring (1) expands relative to the sealing ring (3).

Abstract: An adjusting device of a compressor includes guide vanes (2) arranged in the form of a ring around a longitudinal axis (4), which vanes are in each case connected fixedly in terms of rotation to pivot pins (8) and are pivotally mounted in the housing (46). Two-armed cranks (10) are connected fixedly in terms of rotation to the pivot pins (8), cranks (10) neighboring each other in circumferential direction being linked to each other by means of coupling links (24, 26). With a lower overall volume and low use of materials, a jamming, in particular in view of thermal expansions and production tolerances, is to be avoided. For use with a radial-flow compressor, it is proposed to arrange the cranks (10) and the coupling links (24, 26) in an annular space (52) which neighbors the discharge port, into which space the pivot pins (8) parallel to the longitudinal axis (4) protrude with their free ends.

Abstract: The purpose of the invention is a cross flow fan comprising an convergent inlet (2,3,10), an impeller (1) or rotor provided with blades and a divergent (4) delimited by a downstream face (12) of the scroll element and a downstream face (9) of the cross-head element. The inlet and divergent delimit two narrowing longitudinal passages (13, 14). With respect to a reference system of perpendicular axes x and y, the origin of which is located on the axis of rotation of the impeller (1) and whose abscissa X axis is parallel to the downstream face (9) of the cross-head element, it features:an upstream leading edge (6) of the cross-head element describing an angle included between 290.degree. and 330.degree. at a distance from the impeller or an air gap (13) included between 2 and 8% of the outside diameter De of the impeller,a face (7) of the cross-head element describing an angle, the apex of which is one and the same with upstream leading edge (6) of the cross-head, included between -20.degree. and 60.degree.

Abstract: A gas turbine engine rotor (18) and shaft (28) are secured against radial loosening between the shaft (28) and axially spaced rotor spigots (24, 26) by annular spacer rings (42, 43) which are fabricated from a material having a thermal coefficient of expansion significantly higher or lower than the thermal coefficients of the shaft (28) or rotor (18). The ring (42, 43) is pre-assembled during production of the engine in an interference fit with either the rotor hub (22) or the shaft (28), being sized to remain tight with the pre-assembled member over a range of operating temperatures, and becoming more tightly fit with the other member due to differential thermal expansion therebetween.

Abstract: A segmented turbine vane nozzle assembly for a steam turbine has an inner ring and a plurality of vanes with each vane having a base end and a profile tip and a profile tip trailing edge extension portion and each vane base end being attached to the inner ring and extending radially therefrom. An annular outer ring has a plurality of arcuate grooves of predetermined depth therein. The outer ring is mounted concentrically with the inner ring. Each vane profile tip trailing edge extension portion extends into one outer ring arcuate groove. Each of the vane profile tips leading edge portion is attached to the outer ring so that a vane assembly is formed without welding the profile tip trailing edge of the vanes. This reduces flow leakage and the formation of erosion caused by the formation and release of large droplets. A method of making a segmented turbine vane nozzle assembly is also disclosed.

Abstract: The invention relates to a fan unit comprising a tubular external housing which has inlet and outlet connectors placed coaxially one behind in the other. A radial impeller have backwardly directed vanes. A distributor surrounds the radial impeller and positioned downstream thereof. The distributor is secured on an inner side of the housing and having a plurality of guide vanes extending axially and circumferentially spaced around the periphery. The vanes are adapted to deflect the flow of impelled fluid radially emerging from the impeller to an axial direction and which are so inclined at an angle of attack, which is selected in accordance with the direction of emergence of the impelled fluid in relation to the axis of rotation of the radial impeller that a smooth even flow transition takes place in the distributor. The ring of guide vanes coaxially surrounds the impeller with a clearance gap of substantially constant width.

Abstract: Variable stator vane arrangements for compressors of gas turbine engines suffer from errors in the angular position of the variable stator vanes because of relative movement between the stator casing and control ring which is allowed by a clearance between the stator casing and control ring. A plurality of pieces of material which have a relatively high coefficient of expansion are arranged circumferentially and are positioned radially between the control ring and the stator casing. The pieces of material control the effective clearance between the control ring and the stator casing so that the error of the variable stator vane angular position is minimized. The pieces of material may be formed from a polyimide resin or high coefficient of expansion steel, and may be positioned in housings which are secured to the control ring.