Abstract: Embodiments presented provide for a firefighting apparatus and method of fluid dispersion for use during firefighting. In embodiments, a firefighting fluid is proportionally added to a working stream in an instantaneous manner to prevent fire spread and effectively quell fire propagation.

Abstract: A turbine engine can utilize a combustor to combust fuel to drive the turbine, which drives the engine. A fuel nozzle assembly can supply fuel to the combustor for combustion or ignition of the fuel. The fuel nozzle assembly can include a swirler and a fuel nozzle to supply a mixture of fuel and air for combustion. Increasing efficiency and carbon-containing emission needs benefit from the use of alternative fuels, which combust at higher temperatures than traditional fuels, requiring improved fuel introduction without the occurrence of flame holding or flashback.

Abstract: In accordance with at least one aspect of this disclosure, there is provided a method of accelerating a gas turbine engine. The method includes adding torque to a core of the gas turbine engine to accelerate rotation of the core by controlling fuel flow to a plurality of fuel injectors of the gas turbine engine. The method also includes adding torque to the core by powering an electric machine that is operatively connected to the core. In embodiments, controlling fuel flow to the plurality of fuel injectors is based on feedback from the electric machine.

Abstract: A method of operation is provided. The operating method includes: operating an aircraft powerplant with a powerplant performance characteristic at a first setting, the operating of the aircraft powerplant including combusting a first fuel in the aircraft powerplant; receiving a command to operate the aircraft powerplant with the powerplant performance characteristic at a second setting; modeling operation of the aircraft powerplant using a first fuel digital twin of the aircraft powerplant, the operation of the aircraft powerplant modeled to determine a first fuel value of a first operational parameter for the aircraft powerplant when operating the aircraft powerplant with the powerplant performance characteristic at the second setting and combusting the first fuel in the aircraft powerplant; and selecting the first fuel or a second fuel for operating the aircraft powerplant with the powerplant performance characteristic at the second setting based on the first fuel value of the first operational parameter.

Abstract: Systems and methods for an overheating control system for an electrical power harness disposed within an enclosure of an aircraft. The system includes a temperature sensor disposed within the enclosure and communicatively coupled to an electronic processor. The electronic processor is configured to monitor, via the temperature sensor, a temperature within the enclosure, compare the temperature to a predetermined threshold, and adjust a power output provided to one or more supply lines of the harness based on an amount in which the temperature exceeds the predetermined threshold.

Abstract: A method may include receiving a generator power demand (GPD) signal for a gas generator of a gas turbine engine (GTE). The method may also include applying a smoothing filter to the GPD signal to create a smoothed GPD signal. The method may also include determining, using the smoothed GPD signal, a GPD anticipation parameter for controlling fuel flow rate to the GTE. The method may also include outputting a fuel flow rate request to the GTE based on the GPD anticipation parameter and a power turbine speed (NPT) controlled by an NPT governing feedback loop.

Abstract: A combustor includes a liner configured to define a combustion chamber and extending in a longitudinal direction, a transition piece configured to overlap an end of the liner while being spaced apart from the end of the liner at a predetermined spacing distance, the transition piece extending in the longitudinal direction of the liner, and a shroud disposed between the liner and the transition piece and coupled to the liner, in which the liner and an inner surface of the shroud define a cooling flow path, and in which the cooling flow path is formed with a turbulator to allow the air, which flows in the cooling flow path, to flow as a turbulent flow in order to dissipate heat from the liner.

Abstract: The present disclosure generally relates to monolithic superstructures for supporting a rotating shaft coupled to a rotor relative to a stator. An integral superstructure supports the rotating component. The superstructure includes a bearing portion that contacts the shaft. A stator portion, is spaced a critical dimension radially outward, from the rotor. A first annular transfer portion extends axially forward from the bearing to the stator portion. A second annular transfer portion extends axially aft from the stator portion to a mounting flange. The mounting flange connects the superstructure to a frame. The superstructure maintains a critical dimension between the rotor and the stator as the temperature of the superstructure increases. The rotor may be a compressor impeller in a gas turbine engine and the stator may be an aero component that transfers air into a combustor.

Abstract: According to an aspect of the present invention disclosed herein, there is provided a programmable drip irrigation emitter device, comprising: an input port; a gathering chamber; a flow selection knob; an orifice sized to deliver the desired flow rate of water; one or more output ports; an output distribution chamber, wherein the water is splashed against the chamber surface while being redirected and channeled to pass through several diffusor pin arrays used to achieve nearly uniform water flow rate at the output ports; and an external case comprised of a top piece and a bottom piece.

Abstract: A transfer tube system for connecting between a compressor and a bleed unit of a turbomachine includes a valve assembly with at least one inlet. The valve assembly is disposed to control bleed air flow from the compressor through a bleed system. A strut envelopes an interior space and extends between the compressor and the valve assembly. A bleed tube conduit is connected between the port/compressor and the inlet/valve assembly to convey gas between the compressor and the valve assembly. The conduit passes through the interior space of the strut and includes a pair of bellows disposed in the interior space. Between the bellows, the conduit has a central section with a non-circular shaped cross section to enable minimizing the width of the strut.

Abstract: An adaptor for a tungsten inert gas (TIG) welding gas block may include an adaptor body having a first end and a second end, wherein the first end includes a pair of parallel members separated by a receiving slot; the second end comprises a male twist lock post; the first end is configured to securely engage with the TIG gas block; and the second end is configured to engage with a welding lead.

Abstract: An assembly for a turbine engine having a longitudinal axis includes a first structural element and a nut device, the first structural element having a first hole and a second hole, and the nut device having a retainer fixed to an inner face of the first structural element, the retainer comprising at least a first recess and a second recess connected to one another by a connecting element, the first recess and the second recess each retaining a nut respectively aligned with the first hole and the second hole which are formed through the first structural element, the connecting element being, in whole or in part, adapted to compensate for a greater thermal expansion of the retainer than the thermal expansion of the first structural element.

Abstract: A turbomachinery installation for an offshore platform is disclosed. The turbomachinery installation comprises a train system having at least one preassembled power module, and a torque tube baseplate, on which the train system is installed. A supporting baseplate of the power module is coupled with the torque tube baseplate. Also disclosed is a method of assembling a turbomachinery installation.

Abstract: The BTT probe fixing apparatus includes a cooling sleeve inserted into a fixing hole formed in a vane carrier, the cooling sleeve accommodating a BTT probe measuring vibration of a blade therein, and the cooling sleeve having a lower end thereof fastened to the fixing hole. Furthermore, the BTT probe fixing apparatus includes a probe holder having a lower end fastened to a penetration hole formed in a casing and having an inner portion where the cooling sleeve penetrates therethrough and is inserted thereinto such that the cooling sleeve is capable of being slid in the probe holder, the probe holder being configured to move according to thermal expansion of the casing while maintaining the cooling sleeve and the BTT probe in a fixed position relative to the vane carrier.

Abstract: A misting nozzle assembly that includes a manifold having a fluid entry point and a plurality of ports formed therein each of which is fluidly connected to the fluid entry point. A plurality of nozzle is each adapted for attachment within a respective of the plurality of ports.

Abstract: A system for bleeding air from a compressor of an aircraft engine, the system comprises a bleed off valve and a plenum for receiving bleed air from the compressor via the bleed off valve. The plenum has a first outlet for discharging the bleed air from the plenum into the atmosphere, and a second outlet fluidly connected to the compressor for reinjecting a portion of the bleed air into an air intake portion of the compressor. A backflow valve is provided for selectively closing the first outlet of the plenum. The backflow valve has an actuator operable to displace a closure from a closed position to an open position upon a fluid pressure inside the plenum reaching a pressure threshold.

Abstract: An exhaust cone for an aircraft turbomachine, extending along a longitudinal axis and having a radially internal annular wall and a radially external skin delimiting a primary flow path for hot gases and surrounding the internal annular wall, and partitions mounted radially between the external skin and the internal annular wall and intersecting them in a manner that together with the skin and wall delimits acoustic chambers. The exhaust cone can further include at least one seal arranged between a radial end of one of the partitions and at least one among the internal annular wall and the external skin.

Abstract: An aircraft hybrid electrical propulsion (HEP) system includes an electrical system configured to deliver power to a plurality of electrical loads, a propulsion system configured to generate thrust in response to an input power, and an HEP controller in signal communication with the electrical system and the propulsion system. The HEP controller is configured to monitor a load demand of at least one electrical load among the plurality of electrical loads and to actively control the input power to actively control the thrust in response to changes in the load demand.

Abstract: A combustion engine including at least one combustion chamber, a first bleed air supply fluidly coupled to a portion of the combustion engine upstream the combustion chamber, a second bleed air supply fluidly coupled to a portion of the combustion engine downstream the combustion chamber, and a turbomachine comprising a first compressor, a second compressor, and a first turbine mounted to a common shaft, with the first and second compressors in serial flow arrangement. The turbomachine, further comprising an intercooler serially fluidly coupling a portion of the first compressor to a portion of the second compressor.

Abstract: A combustion system for a vehicle having an engine includes a hydrogen fuel system having a fuel source providing a hydrogen fuel, a combustor operable to combust the hydrogen fuel to generate combustion gases, and a fuel delivery assembly operable to deliver the hydrogen fuel from the fuel source to the combustor. A first control system has a first update rate and is operable to control one or more operational aspects of the turbine engine. A second control system is in communication with the first control system and the hydrogen fuel system and has a second update rate faster than the first update rate. The second control system is operable to monitor at least one parameter associated with the hydrogen fuel system and output at least one control signal to the hydrogen fuel system to control the delivery or the combustion of the hydrogen fuel.