Abstract: A self-moving tunnel support canopy includes front arch frame, rear arch frame, forward jack, and support jack disposed under the front arch frame. The front arch frame has front arch beams and front longitudinal beams longitudinally disposed along arch upper surfaces of front arch beams and coupled to all the front arch beams. The rear arch frame has rear arch beams and rear longitudinal beams longitudinally disposed along arch upper surfaces of the rear arch beams and coupled to all the rear arch beams. The front longitudinal beams and the rear arch beams are spacedly disposed, and a spacing is configured between the front arch beam and a front-adjacent rear arch beam. One end is coupled to the front arch frame, and the other end of the forward jack is coupled to the rear arch frame. The front arch beam and the rear arch beam are both arch-shaped beams.

Abstract: The invention relates to a tunnel excavation device, which includes an excavation head, a main body on which the excavation head is rotatably mounted, a motor provided in the main body and rotates the excavation head, and a controller for controlling the motor, wherein the excavation head includes a perforating means formed by maintaining a predetermined interval from the center of a body part, which has a front surface formed in the shape of a circular plate, to the outer surface of the body part, an injection means for injecting water and liquid nitrogen into the hole formed by the perforating means, and a plurality of cutters provided on the surface of the main body for crushing the bedrock.

Abstract: A structure for reducing a tunnel micro pressure wave is provided. The structure includes a hood structure formed in front of an entry of a railroad tunnel; and an air pipe section in which at least one air pipe is provided along the circumference of the hood structure, wherein the air pipe comprises a horizontal introduction section formed to be extended from an internal side of the hood structure toward a longitudinal direction of the hood structure, an outlet section formed on an external side of the hood structure, and an intermediate section connecting the horizontal introduction section and the outlet section through each other.

Abstract: A reciprocating-piston uniflow engine includes a harmonic oscillator inlet valve capable of oscillating at a resonant frequency for controlling the flow of working fluid into the engine. In particular, the inlet valve includes an inlet valve head and a spring arranged together as a harmonic oscillator so that the inlet valve head is moveable from an unbiased equilibrium position to a biased closed position occluding an inlet. When released, the inlet valve head undergoes a single oscillation past the equilibrium position to a maximum open position and returns to a biased return position close to the closed position to choke the flow and produce a pressure drop across the inlet valve causing the inlet valve to close. In other embodiments, the harmonic oscillator arrangement of the inlet valve enables the uniflow engine to be reversibly operated as a uniflow compressor.

Abstract: A method is disclosed for manufacturing a tie shaft for aero or land based gas turbine engine. The method includes flow forming a tie shaft preform to produce a tie shaft. In one example, the tie shaft includes a nickel alloy cylindrical wall having a length to diameter ratio of at least 6:1, wherein the diameter is an average outer diameter. The wall includes a minimum effective strain of 0.3 in/in (7.6 mm/mm), and a grain size is in the range of G4 to G16 per ASTM E112. The wall includes a roll formed threaded surface having a thread roughness of less than 1260 ?in (32 microns).

Abstract: A method of determining a tool path to machine a component, the method comprising the steps of: securing the component to a fixture having a zero point alignment datum, the component and the fixture having respective mobile reference points; aligning the fixture mobile reference points to target reference points on the machine tool; aligning a digitized model of the component to the component mobile reference points; determining the position of the component on the fixture from the component mobile reference points and the fixture mobile reference points; and adjusting a nominal tool path for the machine tool dependent on the position of the component.

Abstract: The present disclosure provides an improved first stage airfoil for a compressor blade having a unique chord length (CD), stagger angle (?) and camber angle (??). The stagger angle (?) and camber angle (??) provide improved aerodynamics while the chord length (CD) provides for reduced airfoil weight.

Abstract: A joint between a first preform component and a second preform component that are constructed for ultimate use in a gas turbine engine is disclosed. A plurality of extended fibers may be integral with the first preform component and be at least partially enveloped by the second preform component. A method for making the component is also disclosed. In one embodiment the method provides a first preform component having extended fibers integral therewith, and supplying a second preform component. The method further includes inserting the extended fibers at least partially into the second preform component body.

Abstract: Embodiments of the present disclosure include a turbomachine having a turbomachine blade and a stationary structural component. The turbomachine blade includes a tip shroud having a leading edge portion where the leading edge portion has a first surface. The stationary structural component is disposed about the turbomachine blade and includes a corresponding portion corresponding to the leading edge portion of the tip shroud, where the corresponding portion has a second surface, where the first surface and the second surface have generally parallel contours.

Abstract: Methods of forming a blade and rendering a blade resistant to erosion includes positioning a backing plate(s) or elongated backing plate(s) adjacent at least one side of a forward face of a leading edge surface of the blade. The methods include depositing an erosion resistant material in a plurality of layers by fusion bonding the erosion resistant material to the forward face of the leading edge surface of the blade. The backing plates providing a template or guide for depositing the plurality of layers of erosion resistant material. The plurality of layers of erosion resistant material form an erosion shield and a leading edge of the blade. Methods include removing the backing plate.

Abstract: A midframe portion (313) of a gas turbine engine (310) is presented and includes a compressor section with a last stage blade to orient an air flow (311) at a first angle (372). The midframe portion (313) further includes a turbine section with a first stage blade to receive the air flow (311) oriented at a second angle (374). The midframe portion (313) further includes a manifold (314) to directly couple the air flow (311) from the compressor section to a combustor head (318) upstream of the turbine section. The combustor head (318) introduces an offset angle in the air flow (311) from the first angle (372) to the second angle (374) to discharge the air flow (311) from the combustor head (318) at the second angle (374). While introducing the offset angle, the combustor head (318) at least maintains or augments the first angle (372).

Abstract: A gas turbine engine is defined wherein the inlet guide vanes leading into a core engine flow path are sized and positioned such that flow paths positioned circumferentially intermediate the vane are sufficiently large that a hydraulic diameter of greater than or equal to about 1.5 is achieved. This will likely reduce the detrimental effect of icing.

Abstract: A turbine including a plurality of stages, each stage including a rotatable disk and blades carried thereby. An annular gap defined between a pair of adjacent rotatable disks. A sealing band is located in opposing sealing band receiving slots formed in the adjacent disks to seal the annular gap, the sealing band including band engagement structure. A disk engagement structure is defined in the pair of adjacent rotatable disks. The disk engagement structure extends axially into the pair of adjacent rotatable disks and circumferentially aligns with the band engagement structure. A clip member is positioned in engagement with the sealing band through the band engagement structure and in engagement with the pair of adjacent rotatable disks through the disk engagement structure. The clip member restricts movement of the sealing band in only a circumferential direction of the slots.

Abstract: A hydrodynamic face seal ring for use in a rotary machine includes a support ring having at least two support ring segments and a radially-extending, first face. The support ring is configured to releasably couple to an inner surface of an outer casing of the rotary machine. The face seal ring also includes a sealing ring substantially concentric with the support ring. The sealing ring includes at least two sealing ring segments and a radially-extending, second face. The sealing ring is releasably coupled to the support ring such that the first face is mated against the second face.

Abstract: An aspirating face seal for use with a rotary machine includes a rotating seal ring including a radially outer surface that includes an oblique portion. A stationary seal ring is coupled proximate the rotating seal ring such that a first gap is defined therebetween. The stationary seal ring is movable along a centerline axis of the rotary machine between an open position and a sealed position, and includes an extension member that extends across the first gap. An auxiliary seal includes at least one seal tooth that includes a seal tooth tip. The at least one seal tooth extends radially inward from the extension member such that a second gap is defined between the seal tooth tip and the oblique portion.

Abstract: A seal arrangement is installed between confronting co-planar portions of a low pressure steam turbine exhaust hood and a circular bulkhead that forms part of an exhaust duct structure of a steam turbine module. The seal arrangement forms a vacuum seal between the interior and exterior of the exhaust hood and comprises a flexible gasket in the form of an annular diaphragm. This diaphragm has a radially inner circumferential portion that seals with the bulkhead, a radially outer circumferential portion that seals with the exhaust hood, and a radially median resilient portion. Sealing is achieved by providing radially inner and outer clamping flanges operative to sealingly clamp inner and outer circumferential portions of the gasket to the bulkhead and the exhaust hood respectively.

Abstract: An apparatus includes a blade clearance detection system. A probe is configured to communication detection frequencies from and gather reflected signals for the blade tip detection system. The probe has an end supported relative to the casing. A material provides a reference point. The blade tip clearance detection system is configured to generate a first detection frequency configured to pass through the material to detect the position of a target structure, generate a second detection frequency configured to reflect from and detect the reference point, and determine a position of a surface approximate to the target structure based upon the reference point.

Abstract: A gas turbine engine has a spool including compressor and turbine rotors connected by a first shaft. The first shaft extends concentrically around a second shaft. The first shaft forward end has a portion with an inner diameter of close tolerance with the second shaft. The second shaft has a region of enlarged diameter located axially aft of the compressor rotor but axially forward of the forward end of the first shaft. The region of enlarged diameter has a diameter greater than the inner diameter of the forward end portion of the first shaft to cause the region of enlarged diameter of the second shaft to engage the first shaft in interference in the event that the second shaft is moved axially aft relative to the first shaft more than a pre-selected axial distance.

Abstract: An embodiment of the present invention is a turbine nozzle baffle including an annular box structure. The turbine nozzle baffle includes a first diaphragm, a second diaphragm, and a static portion of a rotating seal that form a one-piece annular box structure. The first diaphragm extends from an inner diameter of the box structure to an outer diameter of the box structure to form a first axial side. The second diaphragm includes a first portion and a second portion. The first portion extends from the inner diameter to the outer diameter to form a second axial side. The second portion extends toward the first axial side to form the outer diameter. The second diaphragm connects to the first diaphragm at the outer diameter. The static portion of the rotating seal faces radially inward at the inner diameter between the first axial side and the second axial side.

Abstract: A journal housing including a series of housing threads defined on an outer radial surface. The series of housing threads may be adapted to threadably engage a series of casing threads defined on an inner radial surface of a casing. A shoulder may extend radially-outward from the outer radial surface, and the shoulder may be disposable axially-adjacent the casing and adapted to receive at least one first mechanical fastener.

Abstract: A casing is provided having a longitudinal axis of a turbomachine, the axis extending along a rotor. The casing includes at least one jacket part extending along the longitudinal axis and at least one end-face cover. The cover is surrounded by the jacket part at least with a part of the axial extension of the cover. In order to reduce the need for radial clearance, without compromising the availability or safety of the operation of the machine, the cover has radial clearance with respect to the jacket part and at least two separate guide elements of the cover are provided on the jacket part in two different circumferential positions with respect to the longitudinal axis. The respective guide elements are designed such that they block a respective movement of the cover in the circumferential direction at least unidirectionally.

Abstract: An engine-waste-heat utilization device includes a Rankine cycle with a heat exchanger that is configured to recover engine-waste-heat to refrigerant, an expander that is configured to generate power using the refrigerant coming out from the heat exchanger, a condenser that is configured to condense the refrigerant coming out from the expander and a refrigerant pump that is configured to supply the refrigerant coming out from the condenser to the heat exchanger by being driven by the expander, a power transmission mechanism (crank pulley, pump pulley, belt) that is configured to transmit surplus power to the engine when the expander has spare power even if the refrigerant pump is driven, a clutch that is configured to connect and disconnecting power transmission by the power transmission mechanism, and a case provided near a high-temperature part of the engine such that a shaft of the expander and that of the refrigerant pump are coaxially arranged, the clutch, the refrigerant pump and the expander are integr

Abstract: A system for diagnosing malfunctions in a variable valve actuation device is disclosed. The system has a rocker arm assembly that includes: a first arm, a second arm with the first and second arms attached at a first end, a hydraulically operated latch assembly that functions to secure the first arm to the second arm when latched. It also includes a source of pressurized fluid connected to a hydraulic valve that provided fluid high or low pressure fluid to the hydraulically-operated latch. The latch may be operated by a remote device. A control gallery connects the hydraulic valve to the latch. A pressure transducer is positioned within the gallery and is adapted to create a signal indicating the pressure in the gallery.

Abstract: A valve timing control apparatus includes: a first lock mechanism being arranged to lock the vane rotor to a first position between the most retard angle position and the most advance angle position with respect to the housing, and to release the lock; and a second lock mechanism being arranged to lock the vane rotor with respect to the housing, to a second position which is between the most retard angle position and the most advance angle position, and is on the retard angle side of the first position, and to release the lock.

Abstract: An operation control system for a solenoid valve of a combustion engine having at least one solenoid valve to hydraulically couple and decouple actuation forces of a cam with a gas valve of a cylinder. A driving unit operates the solenoid valve, and a first detection device monitors a status of the solenoid valve by supplying a status signal to a control unit during an engine intake cycle phase of the cylinder. A second detection device analyzing a system parameter corresponding to the cylinder and supplying a control signal during an engine cycle phase other than the engine intake cycle phase. The control unit delays the status signal based on the status signal to temporally synchronize the status signal with the control signal, or a secondary control signal based thereon, and compares the status signal with the control signal or the secondary signals with each other using an AND-Function.

Abstract: A hydraulic pressure supply may include a low pressure portion, a high pressure portion, a low-pressure hydraulic pump receiving the oil stored in the oil pan and discharging the low hydraulic pressure to a first low-pressure line fluid-connected to the low-pressure hydraulic pump, a switch valve fluid-connected to the first low-pressure line, and selectively supplying the low hydraulic pressure to the low pressure portion or the high pressure portion, a low-pressure regulator valve connected to the switch valve, a high-pressure hydraulic pump fluid-connected to the low-pressure hydraulic pump through the first low-pressure line, a high-pressure regulator valve fluid-connected to the high pressure line and controlling the high hydraulic pressure supplied from the high-pressure hydraulic pump and the low hydraulic pressure supplied from the low-pressure hydraulic pump to be stable high hydraulic pressure, a second input line connecting the oil pan to the first low-pressure line.

Abstract: An aftertreatment device for reducing nitrogen oxides (NOx), particulate matter (PM), hydrocarbon (HC), and carbon monoxide (CO) generated by a compression-ignition (CI) engine. In this device, lean exhaust air generated in the CI engine is converted to rich exhaust air, and energy used for the conversion is recycled using an energy recovery device. The result rich exhaust air then pass through an oxidation catalyst, where NOx is reduced with CO and HC.

Abstract: In an internal combustion engine, a hydrocarbon feed valve (15) and an exhaust purification catalyst (13) are arranged in an engine exhaust passage. As rich control for making the air-fuel ratio of the exhaust gas which flows into the exhaust purification catalyst (13) rich, cylinder rich control for generating rich air-fuel ratio combustion gas in the cylinder and exhaust rich control for feeding hydrocarbons from the hydrocarbon feed valve (15) to make air-fuel ratio of the exhaust gas rich are used. When the air-fuel ratio of the exhaust gas which flows into the exhaust purification catalyst should be made rich, if the speed of the vehicle is lower than a predetermined speed and the gear position of the transmission is at a predetermined low speed gear position, exhaust rich control is used instead of cylinder rich control.

Abstract: An exhaust treatment component for treating an engine exhaust. The component includes a housing including an inlet and an outlet, and a mixing assembly located within the housing between the inlet and the outlet. The mixing assembly includes a decomposition tube having a first end and a second end. The first end is configured to receive the exhaust from the inlet and is configured to receive a reagent exhaust treatment fluid. A flow reversing device is disposed proximate the second end, and the flow reversing device is configured to direct a mixture of the exhaust and reagent exhaust treatment fluid as the mixture exits the second end of the decomposition tube in a direction back toward the first end, wherein the flow reversing device includes a plurality of deflecting members for intermixing the exhaust and reagent exhaust treatment fluid.

Abstract: A system includes a catalytic reactor configured to mount to a combustor. The catalytic reactor includes a catalyst configured to reduce emissions associated with combustion in the combustor. The catalytic reactor also includes a first and a second sacrificial coating disposed over the catalyst prior to mounting of the catalytic reactor into the combustor, wherein the first and second sacrificial coatings are removable while the catalytic reactor is mounted to the combustor without damaging the catalyst.

Abstract: Various exemplary embodiments relate to a method and apparatus to reduce emissions of target emission gasses such as sulfur oxides, nitrogen oxides, and carbon oxides from combustion exhaust such as marine engine exhaust by gas membrane separation and liquid carrier chemical absorption. The membrane separation system consists of an absorption system containing semi-permeable hollow fiber membranes through which is circulated a liquid absorbent. Exhaust gases contact the exterior surface of the membranes and the target gasses selectively permeate the membrane wall and are absorbed by the liquid carrier(s) within the bore and thereby are removed from the exhaust stream.

Abstract: A vehicle and a method of updating efficiency of a selective catalytic reduction filter (SCRF) of an exhaust treatment system of the vehicle are disclosed. The method includes obtaining an initial calculated efficiency of the SCRF, via a controller, regarding one of a NOx conversion, a reductant absorption, a reductant desorption and a reductant oxidation. The method also includes determining a soot mass estimate in the SCRF representative of an amount of soot collected inside the SCRF and determining a soot correction factor from the soot mass estimate. The method further includes calculating, via the controller, an updated efficiency value of the SCRF by multiplying the soot correction factor and the initial calculated efficiency to update efficiency of the SCRF.

Abstract: A method of estimating an ideal air-fuel ratio in an internal combustion engine, comprises receiving an output of an upstream air-fuel ratio sensor and an output of a downstream air-fuel ratio sensor, the upstream air-fuel ratio sensor being attached to an exhaust gas passage such that it is positioned upstream of a catalyst provided in the exhaust gas passage to purify an exhaust gas, the downstream air-fuel ratio sensor being attached to the exhaust gas passage such that it is positioned downstream of the catalyst; detecting a state in which the catalyst does not store or release oxygen based on the output of the downstream air-fuel ratio sensor; and deciding as an estimated ideal air-fuel ratio in the internal combustion engine an air-fuel ratio detected by the upstream air-fuel ratio sensor when the state in which the catalyst does not store or release oxygen is detected.

Abstract: An exhaust after-treatment system includes an exhaust inlet, an exhaust outlet, and an array of exhaust treatment components disposed in a housing. The housing includes a first connection flange securing the housing to the inlet, a second connection flange securing the housing to the outlet, and a third flange positioned between the first and second flanges. A mounting device is secured to the third flange to independently support the housing relative to the inlet and the outlet.

Abstract: An exhaust gas system 1 for an internal combustion piston engine, having an exhaust manifold 2 having a plurality of manifold tubes Z1-Z4 and an exhaust gas fitting 2.1, and an exhaust gas line element 3 having an exhaust gas pipe fitting 3.1 that can be connected to the exhaust gas fitting 2.1 by the exhaust gas pipe fitting 3.1. The exhaust gas manifold 2 and at least the exhaust gas pipe fitting 3.1 of the exhaust gas line element 3 each have a partition 2.2, 3.2, each forming two separate exhaust gas channels A2a, A2b, A3a, A3b each having a flow axis S2, S3, and comprising an end face 2.2s, 3.2s running transverse to the flow axis S2 in the area of the fitting 2.1, 3.1, wherein the edge segment R1, the edge segment R2, and/or the core segment K of the exhaust manifold 2 at least partially contact the exhaust gas pipe fitting 3.1 in the axial direction when the internal combustion piston engine is in the warm state.

Abstract: A piston assembly includes: a piston skirt; and a piston crown formed by a casting method and coupled to an upper portion of the piston skirt by using a stud bolt, wherein oil galleries are formed between an upper wall of the piston skirt and an upper wall of the piston crown, wherein an annular part having a circular ring shape and a plurality of ribs having a linear shape and radially arranged to form oil channels for flowing cooling oil are formed on the upper wall of the piston crown, and the plurality of ribs are divided into outer ribs and inner ribs by the annular part.

Abstract: A compressor adapted to compress a working fluid includes a housing surrounding a compressor wheel and a backplate connected to the housing and enclosing the compressor wheel within an interior space of the housing. A cooling fluid conduit is fluidly connected between a cooled and compressed source of working fluid downstream of the compressor and the interior space of the housing of the compressor at a location between the compressor wheel and the back plate. A pressure differential created when the compressor is operating draws a flow of cooled, compressed charge into the interior space of the housing, which flow passes over and convectively cools said compressor wheel before mixing with a main compressor flow and being provided back through the compressor outlet.

Abstract: A two stroke engine of a particular configuration can have its power output increased by running bigger pistons and using ports in the piston skirt through which to conduct compressed air within the skirt through short passages in the cylinder housing that conduct the air from within the skirt to above the piston. As a result a larger piston can be used for the same spacing and opening size in the block to save the need to redesign the block and the crankshaft. A position adjuster for the piston moves it axially without rotation of the piston ports out of alignment with inlet ports in the housing. The piston rod is held in the crosshead using a flat to prevent rotation while an adjuster nut that is turned creates axial movement in the piston rod with a lock nut securing the final piston position.

Abstract: In response to activation of a compression release brake when a motor vehicle having a turbocharged internal combustion engine is operating at some elevation above sea level and a turbocharger compressor is operating in a region of an operating map which is creating boost air in an engine intake manifold which would cause the compression release brake to decelerate the vehicle more slowly at that elevation than it would at sea level for the same operating conditions of the vehicle and engine other than altitude, the compression release brake decelerates the vehicle less slowly by causing an exhaust gas recirculation system to reduce at least one of a) mass of exhaust diverted to an intake system of the engine and b) cooling of the diverted exhaust.

Abstract: In a turbine for an exhaust gas turbocharger of an internal combustion engine having a housing part with accommodation space including a turbine wheel and at least one spiral channel via which exhaust gas of the internal combustion engine may flow. The spiral channel has an outlet cross-section via which the turbine wheel accommodated in the accommodation space may be acted on by the exhaust gas, and has at least one blocking member, which is connected to an adjusting part so as to be movable hereby in the peripheral direction of the accommodation space for adjusting the outlet cross-section (AR, AR?, AR,RGR). A bypass duct is provided, via which exhaust gas can bypass the turbine wheel and whose flow cross-section is also adjustable by the blocking member moved the adjusting part.

Abstract: A method for controlling a turbocharger is provided. The turbocharger has a turbine operatively connected to an exhaust of an internal combustion engine, and a compressor operatively connected to an intake of the engine. The method includes determining a boost pressure command for the compressor. The boost pressure command is configured to provide sufficient combustion reactant for the engine. The method includes calculating a compressor power from the determined boost pressure command, and calculating a turbine flow from the calculated compressor power. The method commands the turbocharger to operate at the calculated turbine flow.

Abstract: A variable flow valve assembly is disclosed, and includes a main body and a piston. The main body defines a chamber, an inlet port, an outlet port, and a wall located between the inlet port and the outlet port. The wall defines a metering orifice for selectively allowing a medium to flow from the inlet port to the outlet port. The piston is moveable within the chamber of the main body in a plurality of partially open positions to vary the amount of medium flowing through the modulation orifice.

Abstract: A rotary internal combustion engine includes an arcuate compression chamber, an arcuate expansion chamber, an output shaft, and a piston coupled to the output shaft for movement through the arcuate compression chamber and the arcuate expansion chamber. The piston has a leading end, a trailing end, an inlet valve that is located at the leading end of the piston for receiving a compressible fluid from the compression chamber and an outlet valve that is located at the trailing end of the piston for expelling a combustion gas into the arcuate expansion chamber.

Abstract: A throttle cable locking assembly (16) for a power tool (1), in which the power tool (1) includes a source of power (2) having an internal combustion engine, a machine implement (4) engaged to the source of power (2), and a throttle handle (6) connected to the internal combustion engine for regulating power supply to the machine implement (4). The throttle cable locking assembly (16) includes: a cable assembly (18), the cable assembly (18) including a throttle cable (20) extending from the internal combustion engine, an outer cable (30) extending from the internal combustion engine and enclosing a portion of the throttle cable (20), and an engagement member (36) carried by a first end portion of the outer cable (30); and an adjuster bolt capable of being engaged with the engagement member (36) provided on the first end of the outer cable (30). A locking case (48) is provided for securing one end of the adjuster bolt and a portion of the engagement member (36).

Abstract: A multi-paneled cooling module adapted to be mounted to an engine exterior protects electronic components such as sensors and associated wiring from heat loads of the engine and/or other heat generating engine devices. The module is formed of wall and ceiling panels having a relatively high thermal conductivity, such as aluminum. The cooling module, which includes strategically situated integral coolant passages within several of its panels, is adapted to protect all enclosed electronic components, including electronic pressure sensors, an EGR valve, and all associated wiring and wiring harnesses. For example, the sensors, harnesses, and valve components associated with and proximal to an EGR venturi may be fully protected from overheating, in spite of exposure of those components to massive heat loads generated by the venturi. Finally, the cooling module may incorporate additional cooling accommodation for hydraulic oil cooling if, for example, the EGR valve is hydraulically actuated.

Abstract: A turbomachine including a combustor in which fuel is combustible to produce a working fluid, a turbine section, which is receptive of the working fluid for power generation operations, a transition piece in which additional fuel is combustible, the transition piece being disposed to transport the working fluid from the combustor to the turbine section and a staged combustion system coupled to the combustor and the transition piece. The staged combustion system is configured to blend components of the fuel and the additional fuel in multiple modes.

Abstract: Provided is a structure of a gas turbine engine for extracting a part of compressed air generated by a compressor. The structure comprises a cylindrical housing having an annular portion extending around the compressing chamber to define an annular chamber, an annular partition dividing the annular chamber into first and second plenum chambers. The cylindrical housing has first apertures to communicate between the compressing chamber and the first plenum chamber. The partition has second apertures to communicate between the first and second plenum chambers. The first and second apertures are configured so that that the first apertures have a first total cross-sectional area and the second apertures have a second total cross-sectional area which is smaller than the first total cross-sectional area.

Abstract: A rotary machine is provided with a casing and an atmosphere relief mechanism (20) for closing an opening (12) for atmospheric release formed in the casing and relieving pressure of inner fluid to atmosphere when a pressure in the casing rises. The atmosphere relief mechanism includes: a rupture disc (24) configured to rupture when the pressure in the casing reaches a predetermined pressure; a pair of annular holding parts (22, 27) arranged to hold an outer edge of the rupture disc from both sides; a plurality of fastening members (29) for fastening the pair of annular holding parts to each other so as to hold the rupture disc between the pair of annular holding parts; and an annular spacer part (25) provided along an outer circumference of the rupture disc.

Abstract: A gas turbine engine has an inlet duct formed to have a shape with a first ellipse in one half and a second ellipse in a second half. The second half has an upstream most end which is smaller than the first ellipse. The inlet duct has a surface defining the second ellipse which curves away from the first ellipse, such that the second ellipse is larger at an intermediate location. The second ellipse is even larger at a downstream end of the inlet duct leading into a fan.

Abstract: A gas turbine combustor assembly including a combustor liner and a plurality of fuel nozzle assemblies arranged in an annular array extending within the combustor liner. The fuel nozzle assemblies each include fuel nozzle body integral with a swirler assembly, and the swirler assemblies each include a bellmouth structure to turn air radially inwardly for passage into the swirler assemblies. A radially outer removed portion of each of the bellmouth structures defines a periphery diameter spaced from an inner surface of the combustor liner, and an interface ring is provided extending between the combustor liner and the removed portions of the bellmouth structures at the periphery diameter.