The present invention provides a gas turbine combustor that has a fuel injection nozzle using a fluid other than liquid fuel to atomize the liquid fuel and that can suppress a reduction in power generation efficiency resulting from a heat loss while promoting the atomization of the liquid fuel. The gas turbine combustor is adapted to mix liquid fuel with combustion air led from a compressor, burn the mixture, and supply combustion gas generated to a gas turbine. The gas turbine combustor includes a fuel injection nozzle that atomizes the liquid fuel into fine liquid droplets. The fuel injection nozzle includes a first system adapted to supply the liquid fuel and a second system adapted to supply a fluid for atomizing the liquid fuel. Low-boiling liquid fuel is supplied to the second system as the fluid. The second system is adapted to heat and supply the low-boiling liquid fuel.

Gas turbine combustor

A gas turbine engine assembly (10), includes a core gas turbine engine (12), a low-pressure turbine (14) coupled to the core turbine engine, a counter-rotating fan assembly (16) coupled to the low-pressure turbine, and a booster compressor (24) coupled directly to the low-pressure turbine such that the booster compressor and the low-pressure turbine rotate in the same direction.

Gas turbine engine assembly and methods of assembling same

An aircraft gas turbine engine assembly includes an inter-turbine frame axially located between high and low pressure turbines. Low pressure turbine has counter rotating low pressure inner and outer rotors with low pressure inner and outer shafts which are at least in part rotatably disposed co-axially within a high pressure rotor. Inter-turbine frame includes radially spaced apart radially outer first and inner second structural rings disposed co-axially about a centerline and connected by a plurality of circumferentially spaced apart struts. Forward and aft sump members having forward and aft central bores are fixedly joined to axially spaced apart forward and aft portions of the inter-turbine frame. Low pressure inner and outer rotors are rotatably supported by a second turbine frame bearing mounted in aft central bore of aft sump member. A mount for connecting the engine to an aircraft is located on first structural ring.

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Aircraft engine with inter-turbine engine frame supported counter rotating low pressure turbine rotors

A cooling circuit is provided disposed between a first wall portion and a second wall portion of a wall for use in a gas turbine engine, one or more inlet apertures, and one or more exit apertures. The inlet aperture(s) provides a cooling airflow path into the cooling circuit and the exit aperture(s) provides a cooling airflow path out of the cooling circuit. The cooling circuit includes a plurality of first pedestals extending between the first wall portion and the second wall portion. The first pedestals are arranged in one or more rows.

Method and apparatus for cooling a wall within a gas turbine engine

An apparatus for disrupting cells or viruses comprises a container having a chamber for holding the cells or viruses. The container includes at least one flexible wall defining the chamber. The apparatus also includes a transducer for impacting an external surface of the flexible wall to generate pressure waves in the chamber. The apparatus also includes a pressure source for increasing the pressure in the chamber. The pressurization of the chamber ensures effective coupling between the transducer and the flexible wall. The apparatus may also include beads in the chamber for rupturing the cells or viruses.

Apparatus and method for cell disruption

A high temperature turbine shroud assembly for an aircraft gas turbine engine comprising a plurality of arcuate ceramic blocks arranged in a ring. The blocks are supported by a pair of annular support members which retain the blocks in the assembly. Spring-like fingers associated with the support members apply a preloaded force against a pair of slanted dovetail surfaces on the blocks to force the blocks against rigid stops formed upon the annular support members, thereby establishing their proper radial position within the assembly. The preload applied by the fingers accommodates the thermal expansion differences between the ceramic blocks and the metallic support members. In an alternative embodiment, the blocks are retained between cooperating rigid legs extending from the annular support members and wedged radially inwardly into position by a preloaded spring contacting the back side of the blocks. Heat transfer between the blocks and metallic support members is minimized by providing point or line contact between components, thus reducing the contact area available for heat conduction.

Ceramic turbine shroud assembly

A counterrotating turbine support assembly includes outer and inner rotors having respective outer and inner blades disposed in an outer casing. A mid-frame is disposed forwardly of the rotors and fixedly joined to the outer casing. A rear frame is disposed axially aft of the rotors and is fixedly joined to the outer casing. A forward support shaft is joined at one end to a forward end of the outer rotor and is rotatably supported at an inner end to the mid-frame by a forward bearing. An aft support shaft is joined at one end to an aft end of the outer rotor and is rotatably supported at an inner end to the rear frame by an aft bearing. An intermediate support shaft is fixedly joined at one end to the inner rotor and is rotatably supported at an inner end to the mid-frame by an intermediate bearing.

Counterrotating turbine support assembly

A rotatable turbine frame (48,50) includes annular outer and inner bands (48b,50b) having a plurality of circumferentially spaced apart struts (48a,50a) extending therebetween. An annular drive shaft (48d,50d) is fixedly joined to the inner band (48c,50c) for transmitting output torque therefrom, and the struts (48a,50a) are backwardly radially inclined relative to the direction of rotation of the frame (48,50) so that gas flow between the struts (48a,50a) tends to straighten the inclined struts (48a,50a) to effect a compressive load component therein.

Rotatable turbine frame

A fluid-cooled element for partially defining hot gas flow passage extending upstream and downstream of a minimum area throat. A serpentine conduit of fluid communication with a coolant source routes cooling fluid within the downstream portion of the element wall bounding the hot gas passage to an internal pocket upstream of the throat. The coolant is thereafter exhausted upstream of the throat as a film over the wall. The upstream wall portion is cooled by the known impingement and film-cooling technique resulting in an element wherein all of the coolant enters the hot gas passage in a low Mach number region upstream of the throat, thereby minimizing momentum losses due to mixing. In the preferred embodiment, the passage throat is defined by a plurality of turbine nozzle vanes, the fluid-cooled element comprising a nozzle band thereof. Flanges support the nozzle within a gas turbine engine and are located upstream of the nozzle throat so as to provide a barrier which minimizes coolant leakage downstream of the throat.

Fluid-cooled element

A turbine support assembly includes a turbine rotor joined to a fan shaft through a support shaft. The support shaft is joined to the fan shaft in a V-configuration having first and second legs joined together at an apex and inclined axially apart, with at least the first leg forming an integral part of the fan shaft. The second leg is rotatably supportable to a frame. The V-configuration increases the stiffness of the turbine support to reduce blade tip clearances. The present invention also provides an annular integral bolt heat shield and axial retention apparatus to axially retain bolts used for holding together two rotor elements during assembly when the bolts are otherwise subject to sliding into a closed cavity of the assembled engine or one of its modules. The integral retainer and heat shield engage the bolts disposed through bolt holes in a gas turbine engine rotor shaft so that the bolts remain straight during assembly when a second rotor element such as a second shaft is being attached to the first shaft, and bolt holes in the second shaft have to engage and fit over the bolts of the first shaft. One particular embodiment of the present invention provides a low pressure turbine rotor shaft assembly of a low pressure turbine module wherein forward and aft shafts are attached by bolts which have bolt heads in a closed cavity of the module and are slidably disposed through corresponding bolt holes of each shaft such that the bolt heads are disposed aft of the aft shaft. An integral heat shield and axial bolt retainer is mounted to the aft shaft aft of the bolt heads so as to trap and retain the bolt heads between the shield and the aft shaft.

Ambrose Andreas Hauser

Papers

Ceramic turbine shroud assembly

Counterrotating turbine support assembly

Rotatable turbine frame

Fluid-cooled element

Turbine support assembly including turbine heat shield and bolt retainer assembly