Abstract: A method for cleaning a stationary gas turbine unit during operation, wherein the unit comprises a turbine, a compressor driven by the turbine, the compressor having an inlet, an air inlet duct arranged upstream of the air inlet of the compressor, the inlet duct having a part of the duct adjoining the inlet of the compressor and having decreasing cross section in the flow direction in order to give the air flow a final velocity at the inlet to the compressor. A spray of cleaning fluid is introduced in the inlet duct. The cleaning fluid is forced through a spray nozzle with a pressure drop exceeding 120 bar to form a spray the drops of which have a mean size that is less than 150 ?m. The spray is directed substantially parallel to and in the same direction as the direction of the air flow.

Abstract: A method of cooling a shroud ring in a turbine section of gas turbine engine includes identifying a series of alternating high temperature regions and lower temperature regions of a circumferential temperature distribution about the inner surface of the shroud ring, and impinging cooling air on to an outer surface of the shroud ring. More cooling air is impinged onto regions which correspond to the high temperature regions on the shroud ring than to regions corresponding to the lower temperature regions of the shroud ring.

Abstract: The invention relates to a turbine 1, in particular a gas turbine, which along a swivel-mounted rotationally symmetrical rotor 2 has a compressor 3, a combustion chamber 5 and a turbine section 7 formed of a plurality of turbine stages 15, in which each turbine stage 15 contains mutually interacting blades 17 and vanes 16 which a hot working fluid 13 can flow around, with a coolant provided by the compressor 3 for cooling the blades 16, 17, which can flow in a channel along the rotor 2 from the compressor 3 to the turbine section 7 and into which a liquid can be introduced for cooling. In order to specify a turbine in which less wear occurs and in which the lifetime of the components is increased, it is proposed that the channel extends outside the rotor 2 and that the liquid can be introduced at the end of the channel which faces the compressor 2.

Abstract: In the method for interspersing a gas flow (8) with fluid droplets (5), the fluid droplets (5) are injected in a fluid injection plane into the gas flow (8), characterised in that an auxiliary gas (6.1, 6.2) is simultaneously injected with the fluid droplets (5) into the gas flow (8). The injection speed of the auxiliary gas (6.1, 6.2) is larger than the injection speed of the fluid droplets (5) so that the injected auxiliary gas (6.1, 6.2) stabilises the injected fluid droplets (5) with respect to trajectory and size, partly shields them from the gas flow (8) and/or entrains them into the gas flow (8). By way of this one achieves an improved control of the spatial distribution of the fluid droplets (5) and their size distribution. The fluid droplets (5) penetrate the gas flow (8) more efficiently than without an auxiliary gas (6.1, 6.2). A preferred use is the online wet-cleaning of a gas turbine compressor.

Abstract: A fogging device (26) for introducing water and/or vapor into an intake air flow (10, 27) of a gas turbine (1–3) includes a sound-absorbing device (31, 35). This device may in particular be designed in the form of Venturi tubes (31), the water (29) being fed to the air flow (27) via nozzles (33) arranged at the narrowest location. In this way, the spraying of water for increasing the power output or for generally regulating the gas turbine can at the same time be combined with a silencer, and this in a comparatively simple construction.

Abstract: A silencer (25a) for the attenuation of noise occurring in an intake airstream (10, 27) of a gas turbine (1–3) includes a device or devices (31, 32, 33, 34) for the introduction of water and/or steam into the intake airstream (10, 27). These devices may be designed, in particular, in the form of Venturi tubes (31), the water (29) being supplied, in particular above the saturation limit, to the airstream (27) via nozzles (33) arranged at the narrowest point. In this way, the silencing can be combined at the same time with the introduction of water for increasing the power output or for the general regulation of the gas turbine, this being achieved with a comparatively simple design.

Abstract: A fastener shield for use in a fluid flow path within a gas turbine engine for reducing fluid drag and heating generated by fluid flow over a plurality of circumferentially spaced bolts. The fastener shield has a radially-extending, downstream-facing mounting flange with a plurality of circumferentially spaced bolt holes positioned to receive respective engine mounting bolts therethrough and to attach the mounting flange to elements of the turbine engine. A curved, upstream-facing fastener shield cover is positioned in spaced-apart relation to the mounting flange for at least partially covering and separating an exposed, upstream-facing portion of the bolts from the fluid flow to thereby reduce drag and consequent heating of the bolts. A plurality of closely spaced-apart, spirally-oriented channels are formed in the fastener shield cover for deflecting the fluid flow impinging on the fastener shield cover, thereby increasing the tangential velocity and lowering the relative temperature of the fluid flow.

Abstract: A fluid-flow machine includes at least one rotor and a free number of stators flown by a fluid, with at least one blade thereof positioned on throat-confining surfaces provided with both a device for fluid removal from the flow path and a device for fluid supply into the flow path (bi-functionality). The machine includes at least one line associated with the device for fluid removal for returning the removed fluid to an upstream position in the flow path and at least one further line associated with the device for fluid supply for supplying the fluid from a further downstream position in the flow path.

Abstract: An apparatus having a pressure control system that balances the natural gas flow rate passing through a multi-stage, axial-flow, impulse turbogenerator to produce an electrical power output is provided. The pressure control system includes a primary bypass conduit circuit; pressure regulator valves; modulating valves; and flow sensors. The pressure control system is operatively connected to the multi-stage, axial-flow, impulse turbogenerator. The turbogenerator is operatively connected to both a microprocessor based governor control and a generator for producing electrical output and is preferably contained within a section of bypass conduit that is directly connected to an existing gas distribution pipeline. As the electrical load on the generator and downstream customer demand for gas fluctuate, the pressure control system can provide the proper amount of gas flow through the primary bypass and turbine that is required to produce a predetermined, steady state electrical output.

Abstract: A ventilation device for a high pressure turbine rotor in a turbomachine, the turbine comprising upstream and downstream turbine disks fitted with blades, the device comprising a cooling circuit being supplied by a cooling airflow D taken from the back of the combustion chamber. The circuit is such that the airflow passes through orifices formed in an upstream flange of the upstream disk, such that this airflow circulates in the axial direction towards the downstream side between an inner reaming of the upstream disk and a downstream flange of the downstream disk, the device also comprising a labyrinth inserted between the two disks, such that the airflow is divided into a first flow F1 and a second flow circulating on each side of labyrinth towards the blades.

Abstract: An apparatus having a pressure control system that balances the natural gas flow rate passing through a multi-stage, axial-flow, impulse turbogenerator to produce an electrical power output is provided. The pressure control system includes a primary bypass conduit circuit; pressure regulator valves; modulating valves; and flow sensors. The pressure control system is operatively connected to the multi-stage, axial-flow, impulse turbogenerator. The turbogenerator is operatively connected to both a microprocessor based governor control and a generator for producing electrical output and is preferably contained within a section of bypass conduit that is directly connected to an existing gas distribution pipeline. As the electrical load on the generator and downstream customer demand for gas fluctuate, the pressure control system can provide the proper amount of gas flow through the primary bypass and turbine that is required to produce a predetermined, steady state electrical output.

Abstract: The present invention relates to a system for delivering cooling air to a seal arrangement in a turbine stage of a gas turbine engine. The system comprises at least one vane having a passageway extending from an outer platform of the at least one vane to an inner platform of the at least one vane. A tube insert is positioned within the passageway. The tube insert has an inlet at one end for receiving cooling air from a source of cooling air and an outlet at a second end. A cover assembly is attached to the second end of the tube for receiving cooling air from the tube and delivering the cooling air to the seal arrangement. In a preferred embodiment, the cooling air is pre-swirled in the direction of rotation of a rotor stage of the turbine stage.

Abstract: Suitable means for driving a flow are arranged in annular or ring-segment-shaped cavities that are formed in particular in multi-shell casings of turbomachines. Arranged inside the cavity are ejectors that are supplied via suitable means with a motive-fluid flow which in turn excites the flow, preferably a circumferential flow or a helical flow. The invention is suitable in particular for avoiding casing distortions when turbomachines are at rest.

Abstract: An axial compressor includes a nozzle for injecting a cleaning fluid. The cleaning fluid is injected through the nozzles in a flow duct during operation, so that rear blading rows are also cleaned.

Abstract: A system and method of controlling clearance in a turbomachine includes adjusting the machine case cooling air in response to the difference between the desired clearance and the actual clearance. An accurate estimate of the actual clearance is made with a real time mathematical model on-board engine controller. The model computes thermal growth of the turbomachine components each with a difference equation derived from a closed form solution to the 1st order differential equation obtained through the application of 1st law of thermodynamics. The resulting equation is conveniently formulated in terms of equivalent time constant and steady state growth both correlated with thermo-physical characteristics of multiple fluid streams exchanging heat with the component. The solution is applied over a time step of the control software. Approximating coefficients are strategically placed in the model to allow calibration of the model to a particular version of the engine hardware.

Abstract: Nozzle assembly for injecting a liquid into a process unit through a cross fitting body having at least one of a first and second crossing passageway therethrough with a tubular member carrying a nozzle being injected through one of the cross passageways to position the nozzle carried on the tubular member for the injection of liquid into the processing unit with the liquid being supplied to the tubular member via the other crossing passageway through which liquid is supplied to openings in the tubular member which is in liquid communication with the first crossing passageway to supply liquid to the nozzle.

Abstract: A multi-stage compressor, including a system for the injection of a cooling liquid into at least a portion of the compressor stages to increase the efficiency of the multi-stage compressor by reducing the temperature of the compressed gas produced in the multi-stage compressor. A cleaning solution may also be injected through nozzles used for the injection of the cooling liquid.

Abstract: The inside out gas turbine cleaning method is a new method to clean axial gas turbine compressors. This is done by inserting a specially and fabricated flexible hose with nozzles on it into the first several stages of an off line gas turbine compressor. High pressure hot water with detergent is supplied to the hose and as it is withdrawn from the compressor it blasts dirt from the airfoil surfaces in the compressor. Conventional cleaning sprays water in one direction down the throat of the gas turbine compressor, whereas this method cleans from the back forward giving a different blast angle with higher pressure water (see FIG. 1). Using both the conventional cleaning method and this new process, the compressor can be cleaned better allowing for improved gas turbine power and fuel efficiency.

Abstract: To control the temperature mismatch between the inner and outer bands and covers forming plenums with the inner and outer bands on sides thereof remote from the hot gas path, passages extend from the leading edge of the covers in communication with the hot gases of combustion to the trailing edge of the covers in communication with the hot gas flowpath. A mixing chamber is provided in each passage in communication with compressor discharge air for mixing the hot gases of combustion and compressor discharge air for flow through the passage, thereby heating the cover and minimizing the temperature differential between the inner and outer bands and their respective covers. The passages are particularly useful adjacent the welded or brazed joints between the covers and inner band portions.

Abstract: In a turbine having closed-circuit steam-cooling passages about the rim of the rotor during steady-state operation, compressor discharge air is supplied to the rotor bore for passage radially outwardly into the wheel space cavities between the wheels and spacers. Communicating slots and channels in the spacers and wheels at circumferentially spaced positions enable egress of the compressor discharge air into the hot gas flow path. At turbine startup, cooling air flows through the closed-circuit steam passages to cool the outer rim of the rotor while compressor discharge air pre-warms the wheels and spacers. At steady-state, cooling steam is supplied in the closed-circuit steam-cooling passages and compressor discharge air is supplied through the bore and into the wheel space cavities to cool the rotor.

Abstract: A casing for a gas turbine engine having a longitudinal axis extending therethrough, including a first casing portion having a substantially arcuate section and a split-line flange extending from each end thereof and a second casing portion having a substantially arcuate section and a split-line flange extending from each end thereof. The first and second casing portions are mated at each end by connecting together respective pairs of the split-line flanges. A channel is formed in at least one mating surface of the split-line flanges to provide an axial passage therethrough so that air flow provided to the axial passage reduces a temperature gradient between the arcuate sections and the flanges of the first and second casing portions.

Abstract: An object is to improve the operational reliability of a gas turbine by suppressing thermal stress and thermal deformation acting on the rotor of the gas turbine. The gas turbine has a rotor shaft constructed by arranging, in an axial direction in turn, a plurality of discs each having a plurality of combustion gas-driven moving blades annularly arranged on the peripheral portion and spacers arranged between the discs, and is characterized in that gap portions are formed between a region, on the rotor shaft center portion side, of the above-mentioned discs facing the spacers and spacers adjacent thereto, contact surfaces are formed both of which contact on both a region, on the rotor peripheral side, of the above-mentioned discs facing the spacers and adjacent spacers thereto, and a third flow path leading fluid to the above-mentioned gap portions is provided.

Abstract: An internal combustion engine, particularly suitable for a vehicle, is provided with a plurality of combustion cylinders, a first exhaust manifold, a second exhaust manifold and an intake manifold. Each exhaust manifold is coupled with a plurality of the combustion cylinders. An EGR system is disposed in fluid flow communication between the first exhaust manifold and the intake manifold. A turbocharger includes a compressor having an inlet receiving combustion gas and an outlet in fluid flow communication with the intake manifold. A turbine is drivingly coupled to the compressor, and has a turbine casing and a turbine wheel. The turbine casing defines separate first and second inlet paths for exhaust gas flow from the first and second exhaust manifolds. Efficiency and performance are improved by preserving pulse energy in one exhaust manifold flow, and increasing back pressure in the manifold providing EGR flow.

Abstract: A dual-fluid cooling spray device for use with a steam turbine. The steam turbine includes a casing, a plurality of rotating blades and a plurality of stationary vanes. The dual fluid spray device includes a nozzle adjacent to one row of rotating blades and/or stationary vanes, and a dual fluid housing assembly penetrating the casing and coupled to the nozzle. Both a steam pipe and a water pipe are coupled to the dual-fluid housing assembly.

Abstract: A cooling system for turbomachinery includes a compressor bleed air passageway for supplying bleed cooling air to a plurality of circumferentially spaced, generally axially extending passages in communication with a cavity within the inner barrel in which the flanges of the turbine and compressor rotors are secured to one another. The exit ends of the passages have swirl devices for turning the flow from the general axial direction to a tangential direction corresponding to the direction of rotation of the combined rotors. A leakage seal is provided between the rotor and the stationary component to provide a pressure drop across a plenum and cavity to increase the velocity of air flowing into the cavity. Consequently, cooling air is supplied the cavity at a tangential velocity approaching the rotor velocity with reduced windage and lower temperature, thereby improving the performance of the turbomachinery.

Abstract: A gas turbine includes a first turbine stage having a first guide blade, a first moving blade and a cooling configuration. The cooling configuration has a first cooling-air feed at the first guide blade for cooling the first guide blade, a first cooling-air supply at a first pressure for supplying the first cooling-air feed, and a second cooling-air feed disposed downstream of the first cooling-air feed for cooling the first guide blade. The second cooling-air feed is supplied with a second pressure lower than the first pressure.

Abstract: A turbine engine having improved high pressure turbine cooling is disclosed. In the engine, relatively cool intermediate pressure (P2x) air is diverted from a region of a compressor section and over a high work turbine blade at a lower static pressure than the diverted air to cool the blade. Advantageously, as the diverted air is relatively cool, use of a conventional TOBI nozzle may be eliminated. Similarly, showerheads on the blade may be eliminated. As well, the diverted air may conveniently be used to seal a rear bearing compartment within the engine.

Abstract: A combustion turbine may have a cooling circuit for directing a cooling medium through the combustion turbine to cool various components of the combustion turbine. This cooling circuit may include a compressor, a combustor shell and a component of the combustion turbine to be cooled. This component may be a rotating blade of the combustion turbine. A pressure changing mechanism is disposed in the combustion turbine between the component to be cooled and the combustor shell. The cooling medium preferably flows from the compressor to the combustor shell, through a cooler, the component to the cooled and the pressure changing mechanism. After flowing through the pressure changing mechanism, the cooling medium is returned to the combustor shell. The pressure changing mechanism preferably changes the pressure of the cooling medium from a pressure at which it is exhausted from the component to be cooled to approximately that of the combustor shell.

Abstract: A compressor for a gas turbine engine, comprising a casing having an inner surface defining a plurality of circumferentially spaced-apart grooves adjacent the tips of a row of rotor blades. Each groove as a depth which is less than half the width thereof in order to increase surge margin at off design points without affecting the performance of the compressor under normal operating conditions.

Abstract: A turbine shroud includes a panel having inner and outer surfaces extending between forward and aft opposite ends. The panel includes forward and aft hooks for supporting the panel radially atop a row of turbine rotor blades. The panel includes a plurality of recesses in the inner surface thereof which face tips of the blades. The recesses extend only in part into the panel for reducing surface area exposed to the blade tips.

Abstract: In a turbine rotor, a thermal mismatch between various component parts of the rotor occurs particularly during transient operations such as shutdown and startup. A thermal medium flows past and heats or cools one part of the turbine which may have a deleterious thermal mismatch with another part. By passively controlling the flow of cooling medium past the one part in response to relative movement of thermally responsive parts of the turbine, the flow of thermal medium along the flow path can be regulated to increase or reduce the flow, thereby to regulate the temperature of the one part to maintain the thermal mismatch within predetermined limits.

Abstract: Today, the trend is to increase the temperature of operation of gas turbine engines. To cool the components with compressor discharge air, robs air which could otherwise be used for combustion and creates a less efficient gas turbine engine. The present low thermal expansion sealing ring support system reduces the quantity of cooling air required while maintaining life and longevity of the components. Additionally, the low thermal expansion sealing ring reduces the clearance "C","C'" demanded between the interface between the sealing surface and the tip of the plurality of turbine blades. The sealing ring is supported by a plurality of support members in a manner in which the sealing ring and the plurality of support members independently expand and contract relative to each other and to other gas turbine engine components.

Abstract: An inner shroud 22 is coupled to an outer shroud 20 which receives cooling air through an inlet 54 for flow to the inner shroud. The inner shroud includes a wall 42 which defines in part the hot gas path 16 and a plurality of cavities 44 on an opposite side of the wall. The inner shroud includes a cover 40 having depending compartments 52 with apertures 56 through the floor of the compartments. When the cover overlies the inner shroud body, the compartments are received in the cavities and cooling air from the inlet flows into the compartments and through the apertures for impingement cooling of the inner shroud wall. Spent cooling air exits the inner shroud through passages 45 through circumferential and/or axial facing side walls of the inner shroud and/or the wall of the inner shroud defining the hot gas path.

Abstract: In the present disclosure, an air pipe extends through a stationary blade between outer and inner shrouds. Further, an air passage is directed to a lower portion of the stationary blade and is communicated with the air pipe so that a serpentine cooling passage is formed. The air enters a cavity from the air passage and is discharged to a gas passage through an air hole, a passage and a seal. Thus, the cavity is sealed at a high pressure. Cooling air is supplied from the air passage to a rotating blade through a cooling air hole, a cooling air chamber, a radial hole and a lower portion of a platform. The stationary blade is cooled by the air through the air passage. The cooling air can be supplied to the rotating blade at a low temperature and a high pressure as they are. Accordingly, the air can be also supplied to the rotating blade when a rotor is cooled by vapor.

Abstract: A system for dissolved air floatation treatment of a liquid stream where the system includes a pump having an impeller cavity with input and output ports, and an impeller with an eye disposed adjacent the input port. The impeller draws liquid through the input port and drives the liquid toward the output port and creates a subatmospheric pressure zone in the cavity away from the eye. The pump includes an air introduction port opening into the subatmospheric zone to introduce significant quantities of air into the cavity for mixing with the liquid stream. The system also includes a tank adapted to receive the liquid stream from the pump with dissolved air introduced therein.

Abstract: A gas turbine comprises: a first closed circuit in which cooling gas is supplied to a casing, allowed to pass through stationary blades, and removed to the outside of casing after cooling the stationary blades; a second closed circuit in which cooling air is supplied to the casing, allowed to pass through moving blades, and removed to the outside of casing after cooling the moving blades; a cooler for cooling the cooling gas in the first and second closed circuits; and a booster for pressurizing and circulating the cooling gas cooled by the cooler.

Abstract: An apparatus for controlling vibrations in a rotor stage rotating through core gas flow is provided. The apparatus includes a source of high-pressure gas and a plurality of ports for dispensing high-pressure gas. The rotor stage rotates through core gas flow having a plurality of circumferentially distributed first and second regions. Core gas flow within each first and second region travels at a first and a second velocity, respectively. The first velocity is substantially higher than the second velocity. The ports dispensing the high-pressure gas are selectively positioned upstream of the rotor blades, and aligned with the second regions such that high-pressure gas exiting the ports enters the second regions. The velocity of core gas flow in the second regions consequently increases, and substantially decreases the difference in core gas flow velocity between the first and second regions.

Abstract: In a turbine construction which includes a rotor having at least one radial step formed therein, and at least one packing ring assembly mounted in a stationary turbine component and axially spanning the radial step, a thrust balancing arrangement for the rotor which includes an axial passage in the stationary component extending from a high pressure side of the stationary component and in fluid communication with an area adjacent the radial step on the rotor. A removable restrictor in the passage permits adjustment of the step thrust.

Abstract: In a steam cooled type gas turbine, taking the effect of efficiency and power output into consideration, a rear stage is sufficiently cooled by air in place of cooling all of the stages by steam. In a rotor of the gas turbine having a steam cooled moving blade, a moving blade disposed in a front stage is cooled by steam, and a moving blade disposed at the rear stage is cooled by cooling air through a stationary blade disposed in front of the moving blade at the rear stage.

Abstract: A cooling passage in a turbine blade of gas turbine can be prevented from being blocked by a scale when the turbine blade is cooled by steam. A system for cooling a blade of a gas turbine having a compressor, a combustor and a turbine section comprises a cooling steam supply tube and a steam discharge tube providing communication with a cooling passage in a guide blade of the turbine section, and a cyclone separator provided in the middle of the steam supply tube in proximity to the guide blade.

Abstract: A method for wet cleaning of the nozzle rings of exhaust-gas turbocharger turbines is based on thermal shock of the contaminants, and includes the steps of injecting water in repeated, relatively small amounts, into the exhaust duct immediately upstream of the nozzle ring. A delay between injections allows the nozzle ring to reheat to operating temperature so that each water injection causes a thermal shock. An apparatus to perform the method includes water injection nozzles installed in the exhaust gas casing and a control system. The method and apparatus provide improved cleaning using less water than in known methods.

Abstract: Improved cleaning of the nozzle ring and the moving blades of the axial turbine of a turbocharger is to provided by a cleaning device. The cleaning device (20) includes only one nozzle (21, 44) having at least one injection opening (24) as well as a cleaning-agent feed line (23). The injection opening (24) is arranged at any point (38) of an imaginary circular area (34), which in turn is defined by a center (33) arranged at a distance A upstream of the inner casing wall (11) as well as by a diameter d.sub.k. The center (33) lies on an imaginary parallel area (34) formed at a distance A from the inner casing wall (11). The distance A corresponds to the average diameter of the nozzle ring (8) multiplied by a percentage P.sub.1, (5%.ltoreq.P.sub.1 .ltoreq.30%). The center (33) lies at an intersection point (36) of the parallel area (35) and die flow line (17) intersecting the latter at right angles. The diameter d.sub.

Abstract: An improved water turbine apparatus includes a rotating waterwheel having a plurality of water-receiving buckets arranged about its periphery. Water is delivered to the buckets at a first, upper location and drained from the buckets at a second, lower location. The water is retained in the buckets during rotation between the first and second locations by a curved, fixed turbine wall. A portion of the water delivered to the buckets may be pumped from a well or reservoir, the water drained from the buckets being used to replenish the reservoir. The reservoir can be used to augment a second, variable water source to maintain continuous and consistent turbine output.

Abstract: A gas turbine engine has a plurality of casings defining a chamber exposable to a gasflow therein, and a plurality of retaining members are associated with the housings to retain them against displacement. Each retaining member has an end portion extending into the chamber and a shield is associated with the casings to define a protective cavity within the chamber about the end portions of the retaining members thereby to isolate the end portions from the chamber. A method of assembling a gas turbine engine is also disclosed.

Abstract: An aerodynamically efficient flow transfer device having a means to transfer flow from a static element to a rotor element such that the end of the exit flow is substantially parallel to an exit plane that is perpendicular to the axis of rotation of the rotor and substantially tangential to the operational rotational direction of the rotor. The preferred embodiment provides a cooling air flow transfer apparatus, between a stationary compressor and turbine rotor, having an inducer which includes cooling air flow holes or passages that are acutely angled in a tangential manner to the rotational direction of the rotor. The passages include a cylindrical section leading to a downstream flared outlet in the form of an open channel that has a back wall with a portion that curves to be parallel to the exit plane of the inducer at the channel's end.

Abstract: Cooling air to the 1-2 turbine stage seal is supplied in parallel with air to the second vane surface from a plenum. A modulatable valve in the supply line to the plenum regulates air flow in response to a sensed temperature in the 1-2 seal area. A thermocouple is located in a bypass around a portion of the seal, being radially installed through a hollow vane and an opening in the seal shroud.

Abstract: A fan inlet and diffuser apparatus (30) is provided with a lobed mixer (60) for intermixing fan bypass air (25) with a flow of fan discharge air (27). The fan inlet and diffuser apparatus (30) is particularly adapted for use in a inducing a flow of cooling air (21) through an upstream heat exchanger (20) and thence directing a portion (23) of the cooling air passing from the heat exchanger to the inlet side of the fan (14) of an air cycle machine (10), while directing the remaining portion (25) to bypass the fan (14) and pass into the central outlet flow passage (52) flowing over the mixing ejector (60) which imparts a directional swirl to the bypass flow (25) and a counter swirl to the fan discharge flow (27) passing from the fan outlet through the interior of the mixer (60), thereby enhancing the mixing of these two flows within the passage (52).

Abstract: A system for deforming a turbine stator housing is disclosed which maintains a substantially uniform radial clearance between a stator and a rotor under all operating conditions of a turbojet engine. The system deforms the turbine stator housing so that its longitudinal axis is substantially conincident with the longitudinal axis of the rotor, particularly under transient conditions. Such deformation results in the attainment of equal radial clearance between the rotor and the stator around the periphery of the rotor. The deformation is achieved by heating or cooling a selected portion of the stator housing such that the temperature distribution, measured around a periphery of the stator housing, is non-uniform, such non-uniform temperature distribution causing the stator to radially deform such that is longitudinal axis is coincident with that of the rotor.

Abstract: A windage shield for use with a pair of annular members oriented in an abutting end-to-end arrangement to define one boundary of a fluid flow path, each of the members having a radially extending flange at their respecting abutting ends for coupling the members to each other. The flanges are coupled by a plurality of circumferentially spaced bolts having a head and a nut which protrude into the fluid flow path. The windage shield comprises an annular ring having a first surface with a plurality of circumferentially spaced arcuate grooves formed therein. Each of the grooves is shaped to receive a preselected number of the bolt heads when the ring is positioned against a corresponding flange. A second surface of the ring opposite the first surface includes a plurality of apertures extending through the ring to the first surface with each of the apertures being located between a respective adjacent pair of the arcuate grooves. Each aperture has a countersunk portion on the second surface.

Abstract: A method for enhancing the thermal response of the engine case and annular shroud during the transient response period following a step change in engine power provides for the temporary reduction or elimination of the flow of cooling air supplied to the engine case by the active clearance control system. An alternate method additionally substitutes a flow of relatively warm air to further increase the response of the case.