Abstract: Provided is a method for enabling high-density air to be efficiently manufactured without unnecessarily increasing the pressure and temperature. A method for manufacturing high-density air according to the present invention includes: mixing raw air A with fine water particles W to generate water-containing air A1 having a lower pressure than the raw air A; supplementing the water-containing air A1 with a differential pressure between the pressure of the raw air A and the pressure of the water-containing air A1; and consequently promoting vaporization of the fine water particles W in the water-containing air A1 and reducing the volume of the water-containing air A1 to manufacture high-density air A2. The density of air can be efficiently increased with this method.

Abstract: The gas turbine combustor liner can delimit a combustion chamber, and have at least one monolithic ceramic block having a first face exposed to the combustion chamber and a second face opposite the first face, and a 3D fabric of ceramic fibers partially embedded inside the monolithic ceramic block, and partially extending outside the second face of the monolithic ceramic block, away from the combustion chamber.

Abstract: A method for gathering flight load data for a gas turbine engine includes providing a plurality of blocker doors rotatably mounted to a translating sleeve and a plurality of blocker door islands, each blocker door island disposed between circumferentially adjacent blocker doors of the plurality of blocker doors and mounted to at least one mounting point of the translating sleeve, wherein a blocker door island of the plurality of blocker door islands is a data acquisition unit; and connecting the data acquisition unit to at least one sensor in communication with the translating sleeve.

Abstract: An assembly is provided for a turbine engine. This assembly includes a primary duct, a bleed duct, a plurality of secondary ducts, a heat exchanger and a flow regulator. The bleed duct extends from a bleed duct inlet to a bleed duct outlet. The bleed duct inlet is fluidly coupled with the primary duct. The secondary ducts are arranged in parallel between the bleed duct outlet and the primary duct. The secondary ducts include a first duct and a second duct. The heat exchanger is configured with the second duct. The flow regulator is configured to direct at least a majority of fluid flowing through the bleed duct outlet to: (A) the first duct during a first mode of operation; and (B) the second duct during a second mode of operation.

Abstract: Testable, redundant pneumatic control assemblies and related systems and methods are described herein. An example pneumatic control assembly described herein includes first, second, and third parallel supply channels between a compressed air supply and valve header, first, second, and third parallel vent channels between a vent and the valve header, and first, second, third, fourth, fifth, and sixth logic valves. The first and sixth logic valves are disposed in the first parallel supply channel and the first parallel vent channel, the second and third logic valves are disposed in the second parallel supply channel and second parallel vent channel, and the fourth and fifth logic valves are disposed in the third parallel supply channel and third parallel vent channel. The pneumatic control assembly also includes a first, second, and third solenoid valves to control certain ones of the logic valves.

Abstract: A method for operating a gas turbine engine includes receiving data indicative of an operational vibration within a section of the gas turbine engine; and providing electrical power to a shaker mechanically coupled to one or more components of the section of the gas turbine engine to generate a canceling vibration to reduce or minimize the operational vibration within the section of the gas turbine engine.

Abstract: A gas turbine engine has a first spool having a low pressure compressor section disposed forward of an air inlet along a direction of travel of the engine, and a low pressure turbine section disposed forward of the low pressure compressor section and drivingly engaged thereto. A second spool has a high pressure compressor section disposed forward of the low pressure compressor section, and a high pressure turbine section disposed forward of the high pressure compressor section and drivingly engaged thereto. The high pressure turbine section is disposed aft of the low pressure turbine section. An output drive shaft drivingly engages the low pressure turbine section and extends forwardly therefrom to drive a rotatable load. A method of operating a gas turbine engine is also discussed.

Abstract: A disk engine and system configured to provide high power at a reduced axial length is disclosed herein. The disk engine includes a radial compressor, a compressor discharge manifold positioned circumferentially about compressor, a combustion chamber positioned within the discharge manifold and a radial turbine positioned radially inward of the combustion chamber.

Abstract: A gas turbine engine has a first spool having a low pressure compressor section in fluid communication with an air inlet, the low pressure compressor section including a first plurality of variable guide vanes therein, and a low pressure turbine section drivingly engaged to the low pressure compressor section. A second spool has a high pressure compressor section in fluid communication with the low pressure compressor section to receive pressurized air therefrom, the high pressure compressor section including a second plurality of variable guide vanes at an entry thereof, and a high pressure turbine section drivingly engaged to the high pressure compressor section, the high pressure turbine section disposed upstream of the low pressure turbine section and in fluid communication therewith. An output drive shaft drivingly engages the low pressure turbine section and is adapted to drivingly engage a rotatable load of the gas turbine engine.

Abstract: A propulsion system coupled to a vehicle. The system includes a diffusing structure and a conduit portion configured to introduce to the diffusing structure through a passage a primary fluid produced by the vehicle. The passage is defined by a wall, and the diffusing structure comprises a terminal end configured to provide egress from the system for the introduced primary fluid. A constricting element is disposed adjacent the wall. An actuating apparatus is coupled to the constricting element and is configured to urge the constricting element toward the wall, thereby reducing the cross-sectional area of the passage.

Abstract: A gas turbine combustor is equipped with a transition piece assembly of the combustor, the transition piece assembly includes a transition piece, a frame which is installed on the downstream side (an outlet part) of the transition piece and a seal member which is installed on a coupled part of the aforementioned frame and a turbine-side stator vane part and blocks flowing of compressed air from a compressor into the aforementioned turbine side through a gap of the coupled part, and a projection member is provided on an outer circumference of the aforementioned frame, a movement suppression mechanism for matching the aforementioned projection member and suppressing possible movement of the aforementioned seal member is provided on the aforementioned seal member, the movement suppression mechanism and the aforementioned projection members fit together and thereby the aforementioned seal member is fixed to the frame.

Abstract: A turbomachine includes a compressor and a turbine with a burner and a combustor between the compressor and the turbine. The burner is downstream of the compressor and upstream of the turbine. The burner is connected to the combustor at a front panel of the burner. The front panel includes a frame, a rim extending around a central aperture within the frame, and a seal segment. The frame, the rim, and the seal segment are all integrally formed as a single unitary body.

Abstract: An integrated combustor nozzle includes a combustion liner that extends radially between an inner liner segment and an outer liner segment. The combustion liner includes a forward end portion, an aft end portion, a first side wall, and a second side wall. The aft end portion of the combustion liner defines a turbine nozzle. The integrated combustor nozzle further includes an impingement panel having an impingement plate disposed along an exterior surface of one of the inner liner segment or the outer liner segment. The impingement plate defines a plurality of impingement holes that direct coolant in discrete jets towards the exterior surface of the inner liner segment or the outer liner segment. The impingement panel is radially spaced from the exterior surface to form a cooling flow gap therebetween. The impingement panel includes a collection duct that extends from the impingement panel and defines a collection passage.

Abstract: An assembly is provided for a gas turbine engine. This assembly includes a combustor wall, a case and an inlet. The combustor wall is configured with a quench aperture. The case is displaced from the combustor wall such that a plenum is formed by and extends between the combustor wall and the case. The case includes a case wall, a deflector and a conduit. The deflector projects out from the case wall into the plenum towards the combustor wall. The deflector is arranged upstream of the quench aperture. The inlet to the conduit is arranged next to and downstream of the deflector.

Abstract: The present disclosure relates to systems and methods wherein a dilute hydrocarbon stream can be oxidized to impart added energy to a power production system. The oxidation can be carried out without substantial combustion of the hydrocarbons. In this manner, dilute hydrocarbon streams that would otherwise be required to undergo costly separation processes can be efficiently utilized for improving the power production system and method. Such systems and methods particularly can utilize dilute hydrocarbon stream including a significant amount of carbon dioxide, such as may be produced in hydrocarbon recovery process, such as enhanced oil recovery or conventional hydrocarbon recovery processes.

Abstract: An engine including a motor and a nacelle and a duct between the nacelle and the motor. The nacelle includes a fixed structure, a mobile assembly that is mobile between an advanced position and a retracted position to define a window between the duct and the outside, and a plurality of blades that are mobile in rotation between a stowed position and a deployed position, each one extending on either side of its axis of rotation with a first arm and a second arm. In the stowed position, the first arm is outside the duct and the second arm is inside the nacelle, and where, in the deployed position, the first arm is across the duct and the second arm projects out of the nacelle. With such blades, the flow of air is optimally directed towards the front without it being necessary to provide cascades.

Abstract: A hybrid rocket motor includes a solid fuel element, and an oxidizer tank containing an oxidizer. The solid fuel element adjoins and at least partially defines a combustion chamber in which the solid fuel and the oxidizer are burned, to produce thrust from the hybrid rocket motor. The oxidizer tank is at least partially within the combustion chamber, and the entire oxidizer tank may be within the combustion chamber. The oxidizer tank may be protected by an insulating material, which may also serve as a structural material that contains the pressure of the oxidizer. The insulating material and the fuel material may both be polymer-based materials, although they may be different materials having different characteristics, for example including different additives to the same polymer material. The fuel element and the oxidizer tank may be made by additive manufacturing processes, for example by adding different materials in different locations.

Abstract: A gas turbine engine fuel supply system has a plurality of fuel nozzles fluidly connected to a source of fuel by transfer tubes extending between the fuel nozzles. At least one plug extends between first and second adjacent nozzles of the set of fuel nozzles. The plug has a first end plugging a port on the first adjacent nozzle and a second end plugging another port on the second adjacent nozzle.

Abstract: An object includes an annular outer body having an end and an interior surface; a first annular inner body disposed inside the annular outer body, the first annular inner body having an exterior surface defining a first annular passage with the interior surface of the annular outer body. The first annular passage includes a first plurality of outlets formed on the end of the annular outer body, the first annular passage receiving a coolant and discharging the coolant adjacent the end of the annular outer body. The object also includes a second annular inner body disposed inside the first annular inner body, the second annular inner body defining a second annular passage with the first annular inner body. Further, the object includes a third annular inner body disposed inside the second annular inner body, with the third annular inner body defining a third annular passage with the second annular inner body; and a fourth annular passage opposite and surrounded by the third annular passage.

Abstract: Combustion sections and sealing systems for fuel ignition assemblies of gas turbine engine combustion sections are provided. For example, a sealing system comprises a ferrule positioned on an outer surface of a ceramic matrix composite (CMC) combustor liner an aperture defined in the CMC liner; a sleeve positioned within an adapter of the fuel ignition assembly such that an inner end portion of the sleeve is in contact with the ferrule, the sleeve having an end wall that forms an inner boundary of a cavity defined by the sleeve; and a biasing member positioned within the cavity. The biasing member extends between a bushing and the end wall of the sleeve. The biasing member continuously urges the sleeve into contact with the ferrule to seal the aperture against fluid leakage therethrough. The exemplary sealing system may be part of a fuel ignition assembly of a gas turbine engine combustion section.