Abstract: A cooling fan (100) includes a frame (10), a circuit board (20) and a rotor (30). The frame includes a housing (12) and a plate (14) connecting with the housing. The circuit board is mounted on the plate. The rotor is received in the housing and includes a hollow hub (32) and a plurality of blades (38) extending from the hub. A plurality of light emitting diodes (40) is mounted on the circuit board. When the rotor rotates, each LED projects light towards the rotor and to the frame so that the light will be reflected and deflected by the fan whereby the whole fan glows and produces a fantastic visual effect.

Abstract: A compression system is disclosed, the compression system comprising a stator stage having a row of a plurality of stator vanes arranged around a centerline axis, each stator vane having a vane airfoil and at least one plasma actuator located on the stator stage. Exemplary embodiments of a detection system for detecting an instability in a compression system rotor and a mitigation system that facilitates the improvement of the stability of the rotor are disclosed.

Abstract: A turbine engine cooling arrangement includes a core passage for receiving a core flow for combustion, a first airflow source including a first passage adjacent the core passage for conveying a first airflow, and a second airflow source including a second passage adjacent the first passage for conveying a second airflow. A heat exchanger is thermally connected with the first passage and the second passage for transferring heat between the first airflow and the second airflow.

Abstract: An apparatus for distributing a fluid in a gas flow path inside a turbomachine, comprising: a device for introducing the fluid into the gas flow path; and wherein the device is positioned within the gas flow path. A method for installing an apparatus that will distribute a fluid in a gas flow path inside a turbomachine, the method comprising: machining a casing groove along an inner surface of a casing; machining at least one port into the casing that is in fluid communication with the casing groove; machining an internal cavity in at least one stator blade that is in fluid communication with the casing groove; machining at least one orifice, that is in fluid communication with the internal cavity, on an orifice surface of the stator blade; and coupling a fluid supply to the at least one port.

Abstract: A shroud segment of a turbine shroud of a gas turbine engine comprises a platform with front and rear legs. The platform defines a plurality of axially extending holes with individual inlets on an outer surface of the platform for transpiration cooling of the platform of the turbine shroud segment.

Abstract: Passive shroud cooling of rotor blades (5) is accomplished by a multitude of cooling-air flows introduced into the hot-gas flow upstream of the rotor blades on the outer circumference, these cooling-air flows, depending on the aerodynamic and geometrical conditions, being orientated at a defined radial angle and a circumferentially related tangential angle such that the cooling air primarily and essentially hits the thermally highly loaded bottom surface (11) of the outer shrouds (6) allover. In the apparatus for the performance of the method, cooling air passages (9) tangentially and radially orientated to the hot-gas flow are provided in an area of a casing section (3) which protrudes beyond the stator blades (1) in the downstream direction, this casing section (3) interrupting the transport of cooling air in the axial direction.

Abstract: A heat-dissipating mechanism for a motor includes a rotor and a stator base. The rotor rotates with respect to the stator base and includes a casing and a hub. The casing has a side portion and a bottom portion, and at least one opening is disposed at the bottom portion. The hub is disposed on the casing, for preventing an external particle from entering the rotor. The hub includes a plurality of separation ribs and when the hub is disposed on the casing, a heat-dissipating passage is formed between every two adjacent separation ribs and the side portion of the casing.

Abstract: A rotor (38) for a gas turbine engine (10) has a low emissivity surface finish, or high emissivity surface finish (44), on at least a portion of its surface (42) to reduce temperature differentials between an upper portion and a lower portion of the rotor (38). This reduces bowing of the rotor (38) to allow the gas turbine engine (10) to be started without harmful vibrations of the rotor (38).

Abstract: A turbine generator system, having: a rotatable base; and a plurality of rotor vanes extending from the rotatable base, wherein each of the rotor vanes have helical tapered inner and outer surfaces, and wherein each of the rotor vanes is curved to catch flow perpendicular to the axis of rotation of the rotatable base and to direct the flow into a vortical flow between the inner surfaces of the rotor vanes.

Abstract: A gas turbine engine generally includes a compressor, a combustor, and a turbine. The turbine can include an integrated manifold comprising a plenum defined by a manifold disposed in connection with a divider plate and opposite a shielding plate comprising a plurality of apertures. During operation of the gas turbine engine, a quantity of working fluid enters the integrated manifold and circulates throughout the plenum and shielding plate, and enters the turbine through the apertures to actively control clearances between turbine engine components.

Abstract: In a centrifugal fan the diameter of the impeller is rendered less than 20 mm, yet by rotating it under rotational conditions in which the centrifugal force along the impeller periphery is 10,000 m/s2 or more, the static pressure that the fan generates is heightened. At the same time, rendering the vane spacing a predetermined width or less reduces noise. Configuring in this way produces a small-scale, high-static-pressure, low-noise fan for cooling electronic devices. Furthermore, by mounting the centrifugal fan on a heatsink having densely arranged heat-dissipating projections a small-scale, high-cooling-capacity, quiet cooling device is realized.

Abstract: A rotor of a thermally loaded turbomachine, in particular of a compressor or a gas turbine, is mounted such that it can rotate about a rotor axis and is concentrically surrounded by a hot-gas duct or cooling-air duct. A significant improvement to the ability of the rotor to withstand thermal loads is achieved, with little increased outlay in terms of materials, by virtue of the fact that the rotor comprises a rotor core made of a first material, that the rotor core is concentrically surrounded by shielding rings made of a second material, which shield the rotor core from the temperature in the hot-gas duct or cooling-air duct, the second material having a higher heat resistance than the first material, and that the shielding rings are cohesively joined to the rotor core.

Abstract: A centrifugal air blower guides returning air from a fan rotated by a rotational drive source out of interference with air delivered by a fan. The centrifugal air blower includes a rotational drive source having a rotational drive shaft, a housing including a holder which holds the rotational drive source in surrounding relation thereto, and a fan coupled to the rotational drive shaft of the rotational drive source. The housing has a disk-shaped flange extending from the holder, and the flange has a plurality of air guides disposed on a surface thereof and extending toward a peripheral edge of the flange.

Abstract: The invention is a method for controlling blade tip clearance in a turbine engine having a flowpath extending therethrough, and a system for carrying out the method. The method includes acquiring a first nonpulsating pressure signal PC representative of tip clearance, sensing a second pressure PB substantially unaffected by tip clearance, forming an actual ratio of the acquired pressure and the sensed pressure, determining an error E having an actual component and a desired component, the actual component being a function of the actual ratio; and commanding a clearance control system to reduce the error.

Abstract: Described is a cooled gas turbine guide blade for a gas turbine, with a hollow blade profile which comprises an onflow edge onto which a working medium is capable of flowing, and with, for guiding a cooling medium, an onflow edge duct running inside the blade profile along the onflow edge. Furthemore, to the use of such a gas turbine guide blade and to a method for operating a gas turbine with an abovementioned gas turbine guide blade. In order to provide a gas turbine guide blade with an increased lifetime by means of the invention, it is proposed that, in the onflow edge duct, an electrical heating element be provided, which extends approximately completely over the entire length of the onflow edge duct and through which a heating current flows, before the operation of the gas turbine, for the preheating of the gas turbine guide blade.

Abstract: A computer comprising a chassis supporting an electronic component. A fan housing with an axial duct is mounted to the chassis. A blade assembly is rotatably disposed within the duct and comprises a plurality of fan blades that extend radially from a hub to a fan diameter. The axial duct has a chord length at least equal to the fan diameter.

Abstract: A drain pump is provided that reduces the operating noise when the head is low. The drain pump has a pump casing, and an impeller. The pump casing has a drain inlet for sucking in drain water at a lower end part and a drain outlet for discharging drain water at a side part. The impeller has a shaft part extending in a vertical direction inside the pump casing, a main blade disposed on the outer circumferential side of the shaft part, an auxiliary blade disposed on the lower side of the main blade, and a disc shaped dish part disposed between the main blade and the auxiliary blade. The dish part has an annular partition part extending upward from the outer circumferential edge part of the main blade, which is disposed at a position lower than the upper end part of the partition part.

Abstract: A device for effecting heat transfer to rotating equipment, in particular gas turbines, is provided. A gas turbine (10) comprises a first rotating unit (11), i.e. an internal shaft and a second fixed unit (16), i.e. a housing. A third rotating unit (14, 17), i.e. rotor blades and plates connected to the rotor blades are disposed between the first unit (11) and the second unit (16). The first (11) and third (14, 17) units are rotatable around a common axis (12) and with respect to each other. At least one device (21) for improving heat transfer by convection is assigned to the first rotating unit (11), i.e. the internal shaft.

Abstract: An apparatus for distributing a fluid in a gas flow path inside a turbomachine, comprising: a device for introducing the fluid into the gas flow path; and wherein the device is positioned within the gas flow path. A method for installing an apparatus that will distribute a fluid in a gas flow path inside a turbomachine, the method comprising: machining a casing groove along an inner surface of a casing; machining at least one port into the casing that is in fluid communication with the casing groove; machining an internal cavity in at least one stator blade that is in fluid communication with the casing groove; machining at least one orifice, that is in fluid communication with the internal cavity, on an orifice surface of the stator blade; and coupling a fluid supply to the at least one port.

Abstract: An apparatus and method for active gap monitoring for a continuous flow machine, in particular an aircraft propulsion device, which has a rotor and a housing which surrounds the rotor forming a rotor gap, is disclosed. The apparatus having a cooling channel which is arranged on the external circumference of the rotor housing and is supplied with cooling air from a plenum. The cross section of the cooling channel decreases from the plenum in the circumferential direction. This ensures homogenous cooling and reduces the weight of the apparatus.

Abstract: A turbine rotor 300 includes: a high-temperature turbine rotor constituent part 301 where high-temperature steam passes; low-temperature turbine rotor constituent parts 302 sandwiching and weld-connected to the high-temperature turbine rotor constituent part 301 and made of a material different from a material of the high-temperature turbine rotor constituent part 301; and a cooling part cooling the high-temperature turbine rotor constituent part 301 by ejecting cooling steam 240 to a position, of the high-temperature turbine rotor constituent part 301, near a welded portion 120 between the high-temperature turbine rotor constituent part 301 and the low-temperature turbine rotor constituent part 302. A value equal to a distance divided by a diameter is equal to or more than 0.

Abstract: A leading edge vortex reducing system includes a gas turbine engine airfoil extending in a spanwise direction away from an end wall, one or more plasma generators extending in the spanwise direction through a fillet between the airfoil and the end wall in a leading edge region near and around a leading edge of the airfoil and near the fillet. The plasma generators being operable for producing a plasma extending over a portion of the fillet in the leading edge region. The plasma generators may be mounted on an outer wall of the airfoil with a first portion of the plasma generators on a pressure side of the airfoil and a second portion of the plasma generators on a suction side of the airfoil. A method for operating the system includes energizing one or more plasma generators to form the plasma in steady state or unsteady modes.

Abstract: A method for cooling a shroud segment of a gas turbine engine includes providing a turbine shroud assembly including a shroud segment having a leading edge defining a forward face. A turbine nozzle is coupled to the turbine shroud assembly such that a gap is defined between an aft face of an outer band of the turbine nozzle and the forward face, wherein a lip formed on the aft face is positioned radially inwardly with respect to the gap and extends substantially axially downstream from the gap. Cooling air is directed into the gap. Cooling air exiting the gap impinges against the lip. Post impingement cooling air is directed at the forward face to facilitate forming a film cooling layer on the shroud segment. The film cooling layer is shielded from combustion gases flowing through the gas turbine engine.

Abstract: A method for cooling a turbine shroud assembly includes providing a turbine shroud assembly including a shroud segment having a leading edge, a trailing edge and a midsection defined therebetween. A shroud support circumferentially spans and supports the shroud segment. The shroud support includes a forward hanger coupled to the leading edge, a midsection hanger coupled to the midsection and an aft hanger coupled to the trailing edge. An annular shroud ring structure includes a midsection position control ring coupled to the midsection hanger and an aft position control ring coupled to the aft hanger. Cooling air is extracted from a compressor positioned upstream of the turbine shroud assembly.

Abstract: A method for cooling a shroud segment of a gas turbine engine includes providing a turbine shroud assembly including a shroud segment having a leading edge defining a forward face. A turbine nozzle is coupled to the turbine shroud assembly such that a gap is defined between an aft face of an outer band of the turbine nozzle and the forward face, wherein a lip formed on the aft face is positioned radially inwardly with respect to the gap and extends substantially axially downstream from the gap. Cooling air is directed into the gap. Cooling air exiting the gap impinges against the lip to facilitate film cooling the shroud segment.

Abstract: A fan motor having a small thickness and its impeller's blades formed to have a longer length in the diametrical direction than a width in the axial direction. Since the blade of the fan motor has a tooth structure or chamfers at its edge end in the diametrical direction, turbulence is forcibly evoked in an airflow to promote the turbulent diffusion, thereby suppressing the trailing vortex and reducing the aerodynamic noises, and thus the ventilation efficiency is improved.

Abstract: A turbine airfoil usable in a turbine engine and having at least one cooling system. At least a portion of the cooling system may be positioned in an endwall attached to the turbine airfoil. The endwall may include an endwall horseshoe cooling slot positioned in the first endwall proximate to the leading edge of the airfoil such that one end terminates proximate to the pressure side of the generally elongated hollow airfoil and a second end terminates proximate to the suction side of the generally elongated hollow airfoil. The endwall horseshoe cooling slot may include a plurality of film cooling holes angled to create a film cooling layer to reduce airfoil and endwall temperatures at the intersection between the leading edge of the airfoil and the endwall.

Abstract: A gas turbine section of a gas turbine engine, including a first stage turbine disk, a forward outer seal carried on the turbine disk and a forward shaft cooperating with the first stage turbine disk for transmitting torque generated by the turbine section to a compressor section of the engine. The forward shaft intersects the first stage turbine disk at a non-perpendicular angle in the area of the disk hub for directing sufficient hot air against the disk hub to balance the thermal response rate of the disk hub to the thermal expansion rate of the forward outer seal.

Abstract: A turbine nozzle cooling sub-system is provided. The sub-system includes at least one turbine nozzle segment. The segment includes an arcuate, radially outermost endwall, an arcuate, radially innermost endwall, and at least one airfoil vane. The endwalls each include at least one open passage. The airfoil vane extends between and is coupled to the endwalls. The vane further includes a cavity, a leading edge, a trailing edge, and an airfoil vane external surface. The cavity includes an airfoil vane internal surface and a plurality of turbulators. The cavity and the open passages are in flow communication such that an airfoil cooling air stream flow is facilitated. The sub-system also includes at least one diffuser in flow communication with a compressor assembly and the segment. The diffuser includes at least one diffuser wall and cavity. The diffuser wall extends from the compressor assembly to the segment such that a channeling of the airfoil cooling air stream to the segment is facilitated.

Abstract: A device for lubricating a component in a turbomachine, in particular a shaft bearing in a turbojet, the device comprising an annular support part defining a lubrication chamber around the component, an annular cover mounted in sealed manner on the part and including a lubricating oil inlet, and an annular channel for passing a flow of pressurizing and cooling air, which channel is formed between the part and the cover, and communicates with ducts in the support part and an annular enclosure formed in the cover for passing the pressurizing and cooling air.

Abstract: A fan with central intake comprises a fan frame, a fan wheel and a fan motor. The fan frame provides a hub seat with an annular spacing for fluid flowing through and a joining part at the center of the hub seat for supporting the bearings. The fan wheel is received in the fan frame and provides a hub with an open side and a hollow side with a circular opening. The annular spacing associated with the circular opening constitutes a central flow route for admitting fluid to pass through such that heat from the central area of a radiator under the fan can be dissipated efficiently.

Abstract: A cooler for cooling of electronic components comprises at least two heatsinks thermally connected with each other by heat spreading means, and a double inlet centrifugal blower comprises a casing with two inlets and an outlet, a radial impeller with an axle and an electric drive. The cooler thermally connected with the electronic component. Each of the heatsinks comprises inflow and outflow openings, and thermally connected heat exchanging means and a base. The impeller comprises radial blades located from both sides of an impeller disk. The double inlet centrifugal blower is located between the heatsinks thus each of the outflow openings is coincided with the closest inlet, so cooling air flows through the inflow openings, the heat exchanging means, the outflow openings and the inlets of the blower in a series way.

Abstract: A turbine shroud assembly asymmetrical cooling element such as a shroud segment or a baffle includes an arcuate panel. The panel has a plurality of cooling apertures extending through the panel and an axially extending midline of the panel parallel to an axis of rotation of the arcuate panel. A symmetric portion of the cooling apertures have a symmetrical density of aperture inlets that is symmetric with respect to the axially extending midline. An asymmetric portion of the cooling apertures have an asymmetrical density of aperture inlets that is asymmetric with respect to the axially extending midline. One exemplary cooling element includes a high density area of the cooling apertures in the asymmetric portion having a higher density of aperture inlets than in the symmetric portion. A low density area of the cooling apertures in the asymmetric portion has a lower density of aperture inlets than in the symmetric portion of the cooling apertures.

Abstract: A steam-driven turbine system for a power plant in which a high pressure and a low pressure turbine are coupled to a common shaft to drive an external generator. Process steam supply is used as gland sealing steam for the low pressure turbine and turbine driven steam pumps. The high pressure turbine has glands that are self sealing at higher generator outputs, and thus the turbine utilizes the process steam supply for gland sealing only during startup or at low generator outputs. The excess or “spillover” steam that is produced by the high pressure turbine at higher generator outputs is diverted away from the main condenser and/or low pressure feed heater. The spillover steam, which is normally waterlogged, is first passed through a separator to remove excess moisture. The spillover steam is next passed through a superheater to raise its temperature. The spillover steam is then directed to the low pressure turbine and/or turbine driven steam pumps so that it may be used as gland sealing steam.

Abstract: A system for optimizing cooling air supply pressure includes a high pressure fluid source which receives bleed air from the exit of a high pressure compressor and a nozzle and ejector assembly for supplying fluid to a point of use at a pressure sufficient to maintain a required cooling airflow and backflow margin at the point of use, and for reducing leakage of the cooling fluid between the high pressure source and the point of use.

Abstract: The axial fan for a computer comprises a rotatable fan blade unit and a motor unit. The fan blade unit comprises a fan head and a plurality of fan blades arranged radially thereto. The motor unit is held by supports passing through the airflow. The supports have a distance of at least 7.5 mm from the fan blades measured in axial direction. Due to this distance being larger in comparison to known solutions the fan produces less disturbing noise.

Abstract: A rotary disc pump for pumping fluid materials, comprises a housing having a front and a back wall forming a chamber with a generally coaxial inlet in the front wall and a generally tangential outlet, an impeller is mounted co-axially within the chamber and comprises a shaft mounted in the back wall of said housing and having an outer end extending from the housing and an inner end within the chamber, at least a first circular which is disc mounted on the inner end of the shaft, and at least a second disc which is mounted in axially spaced relation to the first disc and has an opening in the center thereof, arid a conical member which extends co-axially of the shaft from the first disc toward the second disc.

Abstract: An improved air-cooling system for high performance, high density electronic equipment comprises, in one embodiment, a single fan having a radial impeller, a baffle having an inlet portion to efficiently direct air into the fan intake, and a two-tiered outlet plenum to direct one airflow specifically at the highest heat-generating components and another airflow at all components. The air-cooling system is designed to provide maximum cooling for a low-height, high heat-generating electronics module such as a server. By using only a single fan that is matched to the low resistance airflow characteristics of the baffle, the air-cooling system offers significant advantages over multi-fan systems. Also described are a computer server and methods of making heat-dissipation equipment.

Abstract: A turbofan to reduce noise through a suppression of turbulent air flow at an outlet thereof and also to guide the air discharged from the outlet in a specific discharging direction, and an air conditioner equipped with the turbofan to improve an efficiency of a heat exchange. The turbofan includes a rotating plate coupled to a shaft of a drive motor, a plurality of blades radially arranged on a peripheral area of a front face of the rotating plate, a ring-shaped shroud joining to ends of the plurality of blades, and a flow guide rib extending from a peripheral edge of the rotating plate in a rearward direction to guide the air discharged from the turbofan.

Abstract: A cooling fan with dual blade sets has an impeller formed by a rotatable hub, a stator assembly, and a shell. A plurality of mini blades and a plurality of guide blades are respectively formed on a bottom surface and an external surface of the rotatable hub. The impeller has a plurality of holes defined on the bottom surface being arranged in a circle adjacent to the mini blades. Therefore when the impeller rotates, the mini blades are able to drive out the heat in an inner space between the impeller and the shell through the holes to outside.

Abstract: An apparatus for cooling of electronic components of the present invention are provided with a heatsink and a blower with an electric drive. The heatsink comprises a base and heat exchanging means. The electric drive comprises a stator and a rotor with an axle; the stator is rigidly built-in to the heatsink. The blower comprises a radial type magnetized impeller as the rotor. The base provides thermal contact with the electronic component and the heat exchanging means. The base is comprised of at least two layers composite material thereof including at least one layer of electrically insulating material and at least one layer of thermally and electrically conductive material that including the stator.

Abstract: A ribbon drive pumping apparatus and method for substantially incompressible fluids, such as liquids, is disclosed. The pump has an extended tube having an intake at a first end and an outlet at a second end. A ribbon formed of helical coils is mounted in the tube for rotation and the frequency of the coils decreases from the first end to the second end of the tube. Substantially incompressible fluid is collected at the first end, an axial component of velocity is increased via the rotating ribbon, and the substantially incompressible fluid is ejected from the second end to provide pumping of the liquid. Additional fluid is added to an interior portion of the pump, preferably to a low pressure region, for various purposes such as mixing, cavitation prevention, increased throughput, etc.

Abstract: The invention relates to a feed pump for delivering fluid media, wherein the pump bearings are lubricated by the feed medium itself. Connecting channels with valve devices are provided on the suction side and on the pressure side upstream and downstream, respectively, of a displacement element and link the bearing area of the pump with the production channel. Said connecting channels are configured as straight bores in the pump housing. The valve devices are configured as tappets that are disposed in the associated connecting channel sections so as to be displaced while being tight with respect to suction.

Abstract: A heat sink attachment clip for attaching a heat sink assembly to a frame, the heat sink attachment clip includes a pair of attachment brackets. Each attachment bracket has one or more attachment legs and each attachment leg has a clip attachment means for engagement with a corresponding frame attachment means. A levered cam is used to bear on heat sink assembly. The levered cam is moveable from a first position in which the levered cam does not press the heat sink assembly against the frame to a second position in which the levered cam the heat sink assembly presses the heat sink assembly against the frame. A a handle connects the levered cams of the two attachment clips so that movement of the handle engages both levered cams simultaneously.

Abstract: A rotary compressor machine, such as a combustion air charger, includes a rotatable shaft (18) having at least one compressor wheel (20,22) thereon and disposed within a housing (12,14). A donut-shaped heat exchanger (36) is located within the housing (12,14) between the compressor wheel (22) and an outlet (32) from the housing and has radially inner and outer peripheries (40,42). The outer periphery (40) defines an inlet for the heat exchanger (36) for gas discharged by the compressor wheel (20). The heat exchanger is provided with radially inner and outer flow paths defined by tubes (92) and includes a combined manifold and tank (44) which is secured and sealed to a header plate (88) receiving the tubes (92). The combined manifold and tank (44) includes first, second and third axially spaced walls (96,98,100) with each having a central opening (110,112,114).

Abstract: An integrated blade cooler for electronic components comprises a blower with a radial impeller and a casing, an electric drive with a magnetic rotor and a stator, and a heatsink with fins and a base. The casing has an inlet and an outlet; the impeller comprises blades, a backplate disk and an axis of rotation; and the fins are clothed in a cover plate with an outflow opening that being coincided with the inlet. The stator is made as a part of the casing and as a printed circuit board, and the radial impeller comprises magnetic blades serving as the magnetic rotor. At least part of the cover plate is made as a part of the casing thus the outflow opening concise with the inlet.

Abstract: A fan housing of a fan unit includes a housing wall standing from the surface of a printed circuit board. The printed circuit board serves to establish the fan housing in cooperation with the housing wall. The fan housing further includes a ceiling wall connected to the housing wall. The ceiling wall extends along a datum plane parallel to the surface of the printed circuit board. A high speed airflow can be generated within the fan housing. The airflow promotes the heat radiation from the printed circuit board. An electrically conductive wiring pattern extending over the surface of the printed circuit board may further promote the heat radiation from the printed circuit board.

Abstract: Aspects of the present invention relate to hollow elongated turbine engine components, such as transition ducts, having a cooling system. The component can have first and second ends, and can be defined by an outer peripheral wall. The cooling system extends longitudinally within the wall between the first and second ends. While configured to cool the entire component, the cooling system is particularly configured to reduce thermal gradients that can occur in regions proximate to the first and second ends of the component caused by higher loads in those regions. The cooling system can include at least one pair of cooling channels. Each channel pair includes a first channel and a second channel. The first and second channels can be arranged such that a coolant supplied to each channel can exchange heat with itself in at least the region substantially proximate to one of the ends.

Abstract: A screw compressor includes a housing and a screw rotor disposed in the housing and rotatable relative to the housing for compressing a refrigerant, the housing and the screw rotor having a rest condition, and an operating condition wherein at least one of the housing and the rotor deflect from the rest condition, and structure for at least one of reducing deflection from the rest condition and evenly distributing deflection from the rest condition when the rotor is in the operating condition, whereby clearance between the housing and the rotor is optimized in the operating condition.

Abstract: A turbine blade tip clearance control system has a rigid two part outer casing (42) which sandwiches a control ring (48) therebetween, and an air pressurised flexible inner casing (28) which carries shroud segments (22) within it. Struts (40) span the annular space between the casings (42, 28) and prevent flexing of casing (28) until blade tip clearance needs adjusting, whereupon, ring (48) is heated, along with the adjacent portion of outer casing (42) and expands, allowing casing (28) to flex outwards, thus lifting the shroud segments (22) away from the blade tips (24). Closure of the tip clearance is achieved by cooling ring (48), the resulting contraction thereof, via the struts (40), flexing the inner casing (28) and shroud segments (22) inwards, against the air pressure.