Abstract: A radial-flow pump (1), and especially a coolant pump for an internal combustion engine, comprising an impeller (2) provided with vanes (5) and a directing device (4) including at least one temperature- and/or speed-sensitive element for temperature-dependent control of the coolant flow, where at least one impeller vane (5) and/or the directing device (4) is configured as a speed-sensitive element. In order to increase efficiency, the proposal is put forward that the impeller vanes (5) should be elastically deformable by Coriolis forces of the coolant flow, the discharge angles (&agr;), which are preferably defined between impeller vanes (5) and impeller tangential planes (&egr;), decreasing with an increase in speed.

Abstract: This invention relates to a radial-flow pump (1), and especially a coolant pump for an internal combustion engine, comprising an impeller (2) provided with vanes (5) and a directing device (4) including at least one temperature- and/or speed-sensitive element for temperature-dependent control of the coolant flow, where at least one impeller vane (5) and/or the directing device (4) is configured as a speed-sensitive element. In order to increase efficiency, the proposal is put forward that the impeller vanes (5) should be elastically deformable by Coriolis forces of the coolant flow, the discharge angles (&agr;), which are preferably defined between impeller vanes (5) and impeller tangential planes (&egr;), decreasing with an increase in speed.

Abstract: A cooling air flow control device for a gas turbine engine, the cooling air flow control device comprising a component, a cooling passage defined within the component and a shaped memory metal valve, the shaped memory metal valve disposed in the cooling passage to regulate, in use, the flow rate of a cooling air flow supplied, in operation, through the cooling passage wherein the shaped memory metal valve operates by changing shape to control the flow rate of the cooling air flow in response to the temperature of the component.

Abstract: A propeller or fan, in particular a cooling fan, such as for the radiator of a motor vehicle or electric equipment, for civil or industrial plants, comprising shape-memory actuator means to regulate the direction and/or shape of the blades, for example according to variations in temperature.

Abstract: An air-cooled turbine blade (1) is provided in the cavity (5) of the blade body (3) with an insert (6) made of a shape memory alloy. Due to the contraction of the insert (6) after a certain temperature threshold value is exceeded, the cooling system (12) of the turbine blade (1) is enlarged in the interior. The size of the cooling system (12) (effectiveness of the cooling, cooling-air quantity, size of cooling passages) is therefore advantageously dependent upon the ambient temperature.

Abstract: A method for manufacturing and repair wherein a component composed of equiaxed cast or wrought alloys has at least one section joined thereto composed of directionally solidified or single crystal material

Abstract: An air-cooled turbine blade (1) is provided in the cavity (5) of the blade body (3) with an insert (6) made of a shape memory alloy. Due to the contraction of the insert (6) after a certain temperature threshold value is exceeded, the cooling system (12) of the turbine blade (1) is enlarged in the interior. The size of the cooling system (12) (effectiveness of the cooling, cooling-air quantity, size of cooling passages) is therefore advantageously dependent upon the ambient temperature.

Abstract: A fluid moving device (100) includes a rotatable assembly (101), and a plurality of fan blades (102-04) disposed circumferentially around and extending outward from rotatable assembly (101), at least one of plurality of fan blades (102-04) includes shape memory alloy. The fan blade which includes shape memory alloy transforms into a predetermined shape memory state when the fan blade experiences a predetermined temperature which may be as a result of a predetermined temperature of surrounding fluid passing over fan blades (102-04) when rotation of rotatable assembly (101) is at a given speed. The shape memory state increases or decreases volume flow of surrounding fluid when rotatable assembly (101) is rotating at substantially a constant speed. The speed is substantially constant which limits noise generated from fluid moving (100) device while volume flow rate of the fluid moving device is being changed.

Abstract: An air cycle machine (10) has a first stage turbine (60) mounted to a central portion of a common shaft (12), a compressor (50) mounted to the central portion of the shaft (12), a second stage turbine (30) mounted to a first end of the shaft (12), and a fan (40) mounted to a second end of the shaft (12), all for rotation therewith about a longitudinal axis (14). The first and second stage turbines (60, 30) are operative to extract energy from a flow of compressed air for driving the shaft (12), and the fan (40) and the compressor (50), in rotation about the axis (14).

Abstract: Thermally actuated flow diverters for gas turbine engines are provided which include an arrangement of vanes in spaced overlapping array, which direct, e.g. coolant air flow to rotating engine components, each vane having 3 foil components joined at 3 hinge points. That is, a leading foil positioned on the suction side of the vane, a trailing foil pivotably mounted to a rearward portion of such leading foil at a first pivot axis and a third foil positioned on the pressure side of the vane connecting a forward portion of such leading foil and such trailing foil at second and third pivot axes respectively. Either the third foil or the leading foil is fixedly mounted to engine walls of the same material, the other of these two foils defining an actuation link that is expandable and contractable relative to such walls; the third foil having a coefficient of thermal expansion greater than that of the leading foil.

Abstract: A blade tip clearance control arrangement for a compressor of a gas turbine engine comprises a first annular control member which defines a portion of the gas flowpath through the compressor and which is spaced from the tips of the rotor blades by a clearance. The first annular control member is positioned coaxially inwardly of a pair of second annular control members and is secured thereto by a radially resilient annular support member.The first annular control member is formed from a relatively low expansion material and the second annular control members are formed from a relatively high expansion material.

Abstract: The problem of excessive clearances being generated by rub occurring between the tips of turbine blades and the linings on shroud segments which surround the blades is addressed by way of providing a valve 42 of a metal of different coefficient of expansion than the shroud control ring 24. On ground running prior to take off of an associated aircraft, the valve diverts a cooling airflow away from the ring 24, thus causing it to run hot and expand radially. The shrouds 22 are thus moved away from the blade tips 40 and on take off, are sufficiently far away from the tips 42 as to avoid deep penetration of the lining 38 thereby. The higher temperature generated by take off affects the valve 40 and makes it expand rapidly, to open the cooling airflow paths to the ring 24 via the holes 46 and 50.

Abstract: An arrangement for adjusting guide blades by thermal expansion has an expansion rod which has a significantly different coefficient of linear expansion with respect to the supporting housing and is aligned in the circumferential direction of the turbo-engine and is connected with an adjusting ring by way of a step-up lever. As a result, a guide blade adjustment can be achieved easily as a function of the working gas temperature.

Abstract: Disclosed is a temperature-sensing member including a columnar or hollow cylindrical base having a configuration of a circular or polygonal column or a hollow circular or polygonal cylinder; and at least one strip member of a material having a different coefficient of thermal expansion from that of the base, wherein the strip member is provided on at least a portion of an outer peripheral surface of the base at an acute angle with respect to an axis of the base and in such directions as to intersect each other on opposite sides of the base. In a case where two or more of the strip members are provided on the base, the strip members are disposed in mutually different directions with respect to an axis of the base and at an acute angle with respect to the base.

Abstract: Each blade of a blower fan has a parallel wire group for each side whose thermal expansion coefficient is smaller than that of the blade. The two parallel wire groups are provided substantially over the whole area of a suction-side surface and of a discharge-side surface of the blade such that they extend from the front edge of the suction-side surface and from the rear edge of the discharge-side surface outward obliquely to the radial direction of the blade to cross each other on the face and back sides so as to result in the shape of an "X". Due to a difference of thermal expansion coefficient, in a high-temperature state, camber appears on the blade in oblique directions, and the front edge and the rear edge camber in opposite directions; thus, the blade undergoes torsional deformation to largely vary the angle of incidence.

Abstract: A fan blade which makes use of the difference in the thermal expansion coefficient to enable the angle of attack to be variable without a substantial change in the camber quantity and without the need to employ a temperature-sensitive fan clutch. The blade is provided with two plate-like members having a smaller thermal expansion coefficient than that of the blade in such a manner that one of the plate-like members is provided on the suction-side surface of the blade so as to extend from the forward edge portion at the distal end of the blade toward the rearward edge portion at the proximal end of the blade, and the other plate-like member is provided on the delivery-side surface of the blade so as to extend from the rearward edge portion at the distal end of the blade toward the forward edge portion at the proximal end of the blade, that is, the two plate-like members provided on the obverse and reverse surface, respectively, of the blade cross each other in a substantially X-shape.

Abstract: This invention covers elements, such as guide walls, shut-off flaps, flow dividers and vanes, arranged on or in flow ducts energized with compressor and/or fan air, where said elements are variably arranged to suit variable operating states. To achieve extremely accurate, light-weight and uncomplicated actuating kinematics, the elements are designed as memory-alloy components or are nonpositively connected to at least one such component, they are at least partially located at one end and they permit of selective deformation in response to operationally induced over-maximum or under-minimum temperature conditions.

Abstract: A water pump having a pump impeller and a cup-like disk disposed to be movable along a rotation shaft driven by the engine, a space for passing water being formed between the pump impeller and the cup-like disk, the pump impeller and the cup-like disk being engaged each other by the engagement of vanes and grooves formed at least one side of them respectively, the distance between the pump impeller and the cup-like disk being varied according to the change of water temperature or the change of rotation speed of the engine, thereby to make it possible to adjust the water flow rate of the pump.

Abstract: This device provides the diffusor guide vanes with bypass ducts which establish communication between the pressure and suction sides, which can be sealed by means of shut-off elements, which take the form of bimetal components or at least are connected to such a component, and which are deformed flap-fashion as a function of temperature.

Abstract: A variable camber vane particularly suitable for use as a variable stator vane (20) has a secured root (22), a free tip (24) and a working face (26) disposed within and diverting flow of a working fluid, exhibiting temperature-responsive deflection of the tip as respects the root correllative to the temperature of the working fluid, is comprised of a sintered, generally laminar composite of a first amorphous metallic composition as a first vane element (32) and a second amorphous metallic composition as a second vane element (34), wherein the coefficients of thermal expansion for each of the compositions differ; whereby the camber of the vane varies in response to thermal variations of the working fluid.

Abstract: Temperature regulation of an air cycle refrigeration system is achieved by selectively adjusting the turbine stator geometry in response to the temperature of turbine airflow at a desired location. Such adjustment in stator geometry includes the selective positioning of a portion of the stator adjacent the turbine blades thereby controlling the amount of cooling produced by the turbine or the selective opening and closing of bypass ports provided in the turbine stator to control the flow of air through the turbine. Both of these adjustments in stator geometry are effected by an actuator comprising at least two members of differing coefficients of thermal expansion such as a bimetallic element.

Abstract: Temperature regulation of an air cycle refrigeration system is achieved by selectively adjusting the turbine stator geometry in response to the temperature of turbine airflow at a desired location. Such adjustment in stator geometry includes the selective positioning of a portion of the stator adjacent the turbine blades thereby controlling the amount of cooling produced by the turbine or the selective opening and closing of bypass ports provided in the turbine stator to control the flow of air through the turbine. Both of these adjustments in stator geometry are effected by an actuator comprising at least two members of differing coefficients of thermal expansion such as a bimetallic element.

Abstract: A diffuser for a centrifugal compressor or a nozzle assembly for a centripetal turbine comprising a pair of axially-spaced walls defining an annular housing open at its inner and outer peripheries and a plurality of vanes extending between the walls and defining therewith, between adjacent vanes, working fluid passages open to the inner and outer peripheries of the housing, each vane being defined by a pair of partitions having a common edge extending between the housing walls adjacent the inner periphery of the housing and spaced apart circumferentially at positions remote from the inner periphery of the housing.