Abstract: A fuel nozzle manifold comprising a flange, a stem and a swirler is provided. The flange has a first fluid inlet fluidly connected to a radially extending first flow passage, the stem includes at least a first axially extending and only partially circumferentially extending flow channel, and the swirler has at least a first radially extending premix passage. The flange and the stem can comprise a homogeneous component, or two separate components fluidly connecting the first axially extending flow channel to the first flow passage, to form a fluid connection between the flange and the stem, the swirler comprises another component fitted together with the flange and stem component and fluidly connecting the first premix passage and the first flow channel.

Abstract: An engine contains a compressor stage, a plurality of pulse detonation combustors and a rotary inlet valve structure having a plurality of inlet ports through which at least air flows to enter the pulse detonation combustors during operation of the engine. Downstream of the pulse detonation combustors is a turbine stage. Further, the ratio of the pulse detonation combustors to the inlet ports is a non-integer.

Abstract: A flow equalizing override assembly is provided for use in conjunction with a gas turbine engine (GTE) and a fuel divider system. In one embodiment, the flow equalizing override assembly includes a housing assembly, a fuel divider (FD) valve, a remotely-actuatable valve, and a controller. The FD valve includes: (i) a piston slidably disposed within the housing assembly and movable between a default position and a flow equalizing position, and (ii) a control chamber defined by the piston and the housing assembly. The remotely-actuatable valve is fluidly coupled to the control chamber and is configured to selectively adjust the fuel pressure therein. The controller is configured to command the remotely-actuatable valve to adjust the pressure within the control chamber such that the piston moves from the default position to the flow equalizing position after ignition of the GTE.

Abstract: A flame holder for an afterburner duct of a jet engine, including an arm in the form of a gutter forming a cavity, a shield for protecting the cavity of the arm from heat, and an air supply baffle housed in the cavity, is disclosed. The arm, the protective shield, and the air supply baffle are held together by a one-piece spacer shoe.

Abstract: An air cooling hood offset from an exterior of the transition piece to define an air cooling passage between the air cooling hood and the exterior of the transition piece, wherein the air cooling hood comprises a plurality of air outlets disposed along the exterior of the transition piece, and the plurality of air outlets is configured to expel an airflow from the air cooling passage away from the exterior of the transition piece.

Abstract: A nozzle includes first guiding elements (10) circumferentially arranged at a nozzle rim (9). To reduce sound emission while keeping flow losses low, second guiding elements (20) are also circumferentially arranged at the nozzle rim (9), with one of the first and second guiding elements (10, 20) being diffuser-type and the other of the first and second guiding elements (10, 20) being nozzle-type and with both types of guiding elements circumferentially alternating with each other.

Abstract: An annular combustion chamber of a turbomachine is disclosed. The combustion chamber includes two walls of revolution each having an annular groove extending around the longitudinal axis of the chamber and opening out inside the chamber. The groove has in cross section a substantially U or V shape that is splayed towards the downstream end and has lateral annular surfaces that are inclined with respect to the area of the wall at which the groove is situated.

Abstract: A method for determining sensor locations in a gas turbine engine is provided. The said method includes providing a turbine rear frame including a radially inner surface, a radially outer surface and a plurality of circumferentially-spaced struts extending between the inner and outer surfaces, wherein a strut sector is defined between each pair of circumferentially-adjacent struts, providing a plurality of fuel nozzles that are each aligned with a strut sector, selecting one of the plurality of fuel nozzles as a primary index nozzle and positioning each of a plurality of sensors relative to one of the plurality of nozzles using a corresponding positioning angle such that each of the plurality of sensors coincides with a gas flow temperature distribution profile between each pair of circumferentially-spaced nozzles.

Abstract: A propulsion system for a combined aircraft/spacecraft including: a jet engine having a longitudinal axis defined in a direction from a front end at an air intake to a rear end at a jet exhaust: a front end at an air intake to a rear end at the jet exhaust; a rocket engine having a longitudinal axis defined normal to a rear end at a rocket exhaust; a common engine housing having an elongated shape and wherein the jet engine and the rocket engine are configured substantially coaxially and with respective rear ends facing the same direction when the rocket engine is operated.

Abstract: A propulsion system may be operated by determining pressure in a cryogenic liquid tank storing a fluid and cooling the cryogenic liquid tank in response to determining that the pressure is greater than a predetermined value. The cryogenic liquid tank may be pressurized by admitting a gaseous form of the fluid into the cryogenic liquid tank in response to determining that the pressure in the cryogenic liquid tank is less than a predetermined value.

Abstract: An inlet bleed heat system in a gas turbine includes a compressor discharge extraction manifold that extracts compressor discharge air, an inlet bleed heat manifold receiving the compressor discharge air, and a plurality of acoustic dispersion nozzles disposed at an output end of the inlet bleed heat manifold that reduce a velocity of the compressor discharge air in the inlet bleed heat manifold. Noise is generated from the shearing action between the surrounding atmosphere and air jets from orifices. When the air jet velocity is slowed using, for example, a multi-stage ejector/mixer, noise can be abated.

Abstract: Systems and methods involving multiple torque paths of gas turbine engines are provided. In this regard, a representative spool assembly for a gas turbine engine, which incorporates a compressor, a turbine and a gear assembly, includes: a shaft operative to be driven by the turbine; a first spool segment operative to couple the shaft to the compressor; and a second spool segment operative to couple the shaft to the gear assembly. The first spool segment and the second spool segment are not coupled to each other.

Abstract: The invention relates to a combustion chamber of a gas turbine, inside of which a supplied fuel is reacted with supplied combustion air in order to produce a working medium. The inside of the combustion chamber wall is provided with a lining formed from a number of heat shield elements. The or each heat shield element, together with the combustion chamber wall, forms an interior space that can be subjected to the action of a coolant. The aim of the invention is to provide a combustion chamber with a comparatively simple design that has a high system efficiency. To this end, the invention provides that a flow element is placed in the respective interior space while serving to effect a locally specific control of the flow of coolant.

Abstract: The proposed adaptive exhaust nozzle features an innovative use of the shape memory alloy (SMA) actuators for actively control of the opening area of the exhaust nozzle for jet engines. The SMA actuators remotely control the opening area of the exhaust nozzle through a set of mechanism. An important advantage of using SMA actuators is the reduction of weight of the actuator system for variable area exhaust nozzle. Another advantage is that the SMA actuator can be activated using the heat from the exhaust and eliminate the need of other energy source. A prototype has been designed and fabricated. The functionality of the proposed SMA actuated adaptive exhaust nozzle is verified in the open-loop tests.

Abstract: Control and/or drive device for a flying body for ejecting hot gas streams of a combusted fuel combination of at least a first and second component. Device includes a first hollow chamber body structured and arranged to contain first component, a second hollow chamber body structured and arranged to contain second component, a controllable fuel valve arranged between first hollow chamber body and second hollow chamber body to control feed of first component to second hollow chamber body, and a plurality of outlets structured and arranged to eject respective hot gas streams for influencing a flight path of flying body. Second hollow chamber body is formed as a combustion chamber for combusting the at least first and second components within second hollow chamber body to generate respective hot gas streams, and plurality of outlets are connected to the second hollow chamber body.

Abstract: Buzz saw noise propagates through inlet of aviation engine at high power settings. An inlet of aviation engine with blowing slot blowing air grazing over surface of buzz saw lining at speeds higher than inlet mean air flow speed for buzz saw noise control.

Abstract: A combustion system for performing stable combustion and flame stabilization at high altitudes is described. A primary liquid hydrocarbon fuel is atomized and vaporized within the main combustor chamber to produce a primary fuel vapor. When the combustion system operates at a high altitude, a secondary gaseous fuel is fed into the inlet air port such that the secondary fuel mixes with air, thereby enabling the mixture of the air and the secondary fuel to combust in a catalytic reactor to produce high temperature, oxygen-rich gases that flow into the main combustor chamber. Proper proportional amounts of the two fuels are determined as a function of altitude.

Abstract: A fuel controller, and associated method, provides a fuel control output signal to a fuel control actuator to control operations. The fuel controller determines the fuel control output signal based on rotational speed error. A combustion air controller provides a combustion air control output signal to a combustion air control actuator to control operations. A cross channel controller is in communication with the fuel controller and the combustion air controller. The cross channel controller provides a combustion air control modification signal to the combustion air controller. The combustion air control modification signal is determined from the fuel control output signal using an air versus fuel model. The combustion air controller determines a preliminary combustion air control signal based on an exhaust temperature error, and further determines the combustion air control output signal based on both of the preliminary combustion air control signal and the combustion air control modification signal.

Abstract: A bearing like surface on a stationary component reduces deflection of an adjacent rotating component. The stationary component is generally parallel to and offset from a rotational component. The rotational component rotates about a central axis. Protrusions located on the stationary component are in contact with the rotational component to prevent deflection of the rotational component while reducing the friction between the rotational and stationary component. The protrusions have a generally flat surface that may be used to affix the protrusions to the stationary component. An arced surface of the protrusions is in contact with the rotating component. The number, size and the shape of the protrusions are determined by the requirements of the application.

Abstract: A fuel nozzle for a turbine engine has a central body member with a pilot, a surrounding barrel housing, a mixing duct and an air inlet duct. The fuel nozzle additionally has a main fuel injection device located between the air inlet duct and the mixing duct. The main fuel injection device is configured to introduce a flow of fuel into the barrel member to create a fuel/air mixture which is then premixed with a swirler. The fuel/air mixture then further mixes in the mixing duct and exits the nozzle into a combustor for combustion. The geometry of the fuel nozzle ensures that pressure waves from the combustor do not create a time varying fuel to air equivalence ratio in the flow through the nozzle that achieves a resonance with the pressure waves.