Abstract: A starter air valve assembly includes a valve body, a flow control valve, a rate control servo mechanism, and a valve actuator. The valve body defines a flow passage having at least an inlet port and an outlet port. The valve is disposed at least partially within the flow passage and is moveable between an open position and a closed position. The rate control servo mechanism is adapted to receive pressurized fluid and is configured, upon receipt of the pressurized fluid, to supply a controlled flow of the pressurized fluid. The valve actuator is coupled to the valve and is in fluid communication with the rate control servo to thereby receive the controlled flow of the pressurized fluid. The valve actuator is configured, upon receipt of the controlled flow of the pressurized fluid, to move the valve between the closed position and the open position at a substantially controlled rate.

Abstract: A gas turbine engine has a rotor stack carried by a central shaft. A number of retainer segments each have a first surface engaging the rotor stack and a second surface engaging the central shaft so as to transmit a precompression force from the central shaft to the rotor stack.

Abstract: A method for distributing effects of a circumferential hot streak condition in a turbine includes communicating a control signal to a rotator moving a stator ring with the rotator in response to the control signal.

Abstract: A turbine nozzle includes a hollow vane joined to opposite inner and outer bands. The inner band includes a forward lip under the leading edge of the vane, an aft lip under the trailing edge of the vane, and a mounting flange spaced therebetween. An impingement bore extends obliquely and aft from the base of the mounting flange under a corner of the inner band toward the aft lip for impingement cooling thereof.

Abstract: The present invention relates to vacuum pumps and a method for creating and maintaining a high vacuum. A vacuum pump includes a regenerative section and a turbo-molecular section. A common first rotor carries forward-rotating elements of both the regenerative section and the turbo-molecular section. Additionally, a second rotor carries counter-rotating elements of the turbo-molecular section. A first drive rotates the first rotor in a forward rotational direction while a second drive rotates the second rotor in a counter-rotational direction. The drives may be controlled to drive the common first rotor on start-up, and to later drive the second rotor.

Abstract: A turbine stage includes a row of airfoils joined to corresponding platforms to define flow passages therebetween. Each airfoil includes opposite pressure and suction sides and extends in chord between opposite leading and trailing edges. Each platform has a scalloped flow surface including a bulge adjoining the pressure side adjacent the leading edge, and a bowl adjoining the suction side aft of the leading edge.

Abstract: A line cutting device for use with a hydrodynamic propeller has a blade (5) fixed to a vessel having the propeller. Three rotating blades (22) extend from a hub fixed around the propeller's shaft. The fixed and rotating blades are arranged for line shearing action. Each of the rotating blades has four apertures (21) extending from front to back through the blade for passage of water therethrough towards a respective blade of the propeller. The apertures are arranged to alleviate cavitation on the propeller blades.

Abstract: A turbine engine with a turbine shaft which has a number of disks arranged adjacent to one another, to each of which a number of blades are fastened in a star arrangement, wherein these blades can be cooled with at least one coolant which flows through coolant channels inside the blades is provided.

Abstract: A cooling arrangement (17) for supplying a first cavity (9) with a cooling gas, in particular in a gas turbine of a power plant, includes a cooling-gas passage (19) which is formed in a first component (6) and connects the first cavity (9) to a second cavity (10 ). A second component (16 ) bears against a bearing side (15) remote from the second cavity (10 ) and separates the first cavity (9) from a third cavity (12). The second component (16 ) is displaceable within a range of displacement. To improve the cooling effect, an orifice region (20) of the cooling-gas passage (19) is dimensioned and/or positioned in such a way that its orifice cross section (21) projects from the range of displacement to such an extent that it is open at least with a predetermined minimum cross section in any position of the second component (16 ).

Abstract: Methods to make various types of automatically opening hand fans. One embodiment is an automatic compact hand fan. A second embodiment is an automatic standard hand fan. A third embodiment is an automatic sliding hand fan. A fourth embodiment is an automatic double folding hand fan. A fifth embodiment is an automatic interlocking hand fan. A sixth embodiment is an automatic double folding circular hand fan. A seventh embodiment is an automatic encased sliding hand fan. An eighth embodiment is an automatic rolled hand fan.

Abstract: A method facilitates assembling a variable vane assembly for a gas turbine engine including a casing and an inner shroud. The method comprises providing at least one variable vane including a radially inner spindle that includes a groove defined therein that has at least one machined face, and coupling the variable vane radially between the casing and the inner shroud such that at least a portion of the radially inner spindle is inserted at least partially through an opening extending radially through the inner shroud. The method also comprises securing the variable vane to the inner shroud by engaging the spindle machined face with a retainer coupled to the inner shroud.

Abstract: An axial-flow type fan includes a fan housing consisting of an air inlet, an air outlet and an air channel, and a fan wheel consisting of a hub and fan blades. The air channel of the fan housing accommodates the fan wheel which has end-cornered cutting blades proximate the air outlet of the fan housing. When the fan wheel is rotated, the end-cornered cutting blades are able to eliminate air turbulence and air noise in the air outlet of the fan housing.

Abstract: An electric fan comprises a rotary hub comprising a hollow two-layer cylinder including a plurality of units each including: a gap between the layers, an axial first coupling edge abutted on an adjacent unit, an arcuate second coupling edge at its inner end joined with the first coupling edge, two internal ridges, and a rib interconnected the cylinder and a central sleeve; and a plurality of detachable blades comprising a blade section and a base including a raised member, a connecting edge in a joining portion of the blade section and the raised member, two side shoulders, and a forward, downward projection. Each base is inserted into the gap with the shoulders engaged with the ridges, the connecting edge engaged with the second coupling edge, and one side of the raised member engaged with the first coupling edge respectively. Also, each projection is threadedly secured to each rib.

Abstract: An exhaust diffuser unit for a gas turbine engine includes an outer ring, a diffuser cone and vanes, all made from a ceramic matrix composite material. Each vane has end components which have apertures through which a metallic support strut extends. The support strut is rigidly secured at its radially outer end to a diffuser casing, and is slidably but non-rotatably received at its radially inner end in an aperture in a boss provided on a drum. Structural loads between the casing and the drum are transferred through the strut independently of the vane. Gas loads on the vane are transferred to the strut by way of metallic end components.

Abstract: In a lubricant-cooled gas compressor (10) the temperature of separated lubricant returned to the air-side (11) is monitored by a thermostatically controlled restrictor valve (22) which minimises the flow of returned lubricant when temperature is low as on start up or when running on reduced load but increases the flow as the lubricant temperature increases. This will minimise he condensation of water from indrawn air when the temperature of the compressed air is too low to retain the water as vapour, so that the returned lubricant is contaminated with water which will damage the moving components of the air-end.

Abstract: In known delivery systems, a pump chamber and a revolving impeller in the pump chamber rotating about a pump axis, in which protuberances are provided inside the pump chamber on predetermined end walls, it is disadvantageous that the protuberances very and are complicated to make. In the delivery system of the invention, the friction in the pump chamber is reduced and the efficiency is improved by providing spacers, which space the impeller apart from the end walls of the pump chamber. That the protuberances are disposed in at least one ring around the pump axis.

Abstract: A guide device for guiding a variable-pitch blade, in particular in a turbomachine compressor, the blade having a pivot formed by a cylindrical axial shank mounted in a cylindrical housing of a casing and pivotally guided about an axis in said housing by bearings, where the bearings are abutment bearings with conical rollers, the axes of the rollers being substantially perpendicular to the pivot axis of the blade.

Abstract: A method facilitates balancing a gas turbine rotor. The method includes providing a gas turbine rotor including a plurality of turbine blades, wherein at least one turbine blade includes a blade tip shroud that includes a leading edge and a trailing edge that is opposite the leading edge, and coupling a balance clip to the at least one turbine blade. The balance clip includes a first portion having a first length that enables the clip to extend between the tip shroud leading and trailing edges and includes a first hook that couples to the tip shroud leading edge, a shorter second portion that extends only partially from at least one of the tip shroud trailing and leading edges towards the opposite shroud edge, and a second hook that extends between the first and second portions and couples to at least one of the tip shroud leading and trailing edges.

Abstract: A vane assembly 10 suitable for a turbine engine features a refractory vane 12 with an internal cavity 20 and a pair of flexible metallic baffles 26 extending into the cavity from spanwisely opposite ends of the vane. A rigid fastener 48, such as a nut and bolt assembly applies a tensile load to the baffles. The tensile load is reacted out as a compressive load applied to the vane. In another embodiment, the baffle is relatively rigid but the fastener is flexible. The compressive loading exerted on the vane counteracts the brittleness customarily exhibited by refractory materials and imparts damage tolerance to the vane. The arrangement also allows the use of a metal baffle that can be easily secured to the vane and dispenses with any need for a potentially troublesome seal between the baffles and the spanwise extremities of the vane.

Abstract: A hot gas path assembly, suitable for use in the hot gas path of a gas turbine, has as a hot gas duct wall an impact-cooled gas-impermeable element and a transpiration-cooled gas permeable element. The gas-permeable element is a run-on covering for the sealing tip, and the gas-impermeable element is a blade foot of a turbine blade. Coolant is led in series through an impact-cooling element to cool the gas-impermeable element, and through the gas-permeable element for transpiration cooling and, if appropriate, also cools the sealing tip. Coolant thus is utilized particularly efficiently. Subdividing walls are arranged for the lateral subdivision of the coolant path, particularly in the circumferential direction, into segments. Because of the subdivision, in the event of damage to the gas-permeable element in one segment, the other segments remain essentially uninfluenced. Redundant cooling orifices may ensure coolant flow even when flow resistance in a transpiration-cooled element rises.