Abstract: A heat exchanger is disclosed which includes a pressure vessel with an inlet for air, an outlet for air, and a bundle of pipes housed within the pressure vessel for a thermo-vector fluid. A gas/solid separator is provided within the pressure vessel for separating particles drawn by the air.

Abstract: A method for assembling a fuel distribution system for a turbomachine fuel injector includes inserting a liquid fuel distributor into an interior cavity of a shroud to create a liquid fuel distribution circuit between the liquid fuel distributor and the shroud and inserting a gas fuel distributor into the interior cavity of the shroud and into an interior cavity of the liquid fuel distributor to create a gas fuel distribution circuit between the gas fuel distributor and the liquid fuel distributor. The method includes inserting a fuel transfer tube into an outer diameter of the shroud. The method includes brazing or shrink fitting at least one of the fuel transfer tube, the gas fuel distributor, or the liquid fuel distributor to the shroud.

Abstract: A recuperator includes a monolithic heat exchanger core having a first side proximal to a combustor inlet and a turbine outlet, and a second side that includes an exhaust outlet. A compressed air inlet is located on the second side, and a compressed air outlet is located on the first side. The compressed air outlet supplies air to a combustor. A first plurality of passageways connects the compressed air inlet to the compressed air outlet. A turbine exhaust inlet is located on the first side, and a turbine exhaust outlet is located on the second side. A second plurality of passageways connects the turbine exhaust inlet to the turbine exhaust outlet. The first and second plurality of passageways are defined by parting plates that extend radially outward in a spiral pattern that maintains a substantially equal distance between adjacent parting plates.

Abstract: A combined liner and panel for use in a gas turbine engine comprise a ceramic matrix composite panel having a plurality of extending members extending away from a face of ceramic matrix composite panel which will face hot products of combustion. A liner includes a plurality of spring members that apply a bias force biasing the extending members. The spring members bias the extending members on the panel in a direction away from the face of the panel which will face the hot products of combustion. A gas turbine engine, and a method of attaching a ceramic matrix composite panel to a liner are also disclosed.

Abstract: A variable area fan nozzle actuation (“VAFN”) system is disclosed. The VAFN system may include an electrohydrostatic actuator (“EHA”) arranged to translate a VAFN panel relative to a translating sleeve. An electrical coupling may extend between a translating sleeve associated with the VAFN system and the fixed structure. The electrical coupling may be movable so that as the translating sleeve and fixed structure move relative to each other, power may be provided to the EHA by a wiring harness extending across the space between the translating sleeve and the fixed structure and connecting the EHA to an EHA power source.

Abstract: The build-up of carbon deposition on the front face of a combustor heat shield is discouraged by jetting air out from the front face of the heat shield with sufficient momentum to push approaching fuel droplets or rich fuel-air mixture way from the heat shield.

Abstract: An environmental control system includes a low pressure tap at a location on a first compressor section of a main compressor section. The low pressure tap communicates airflow to a first passage leading to a downstream outlet. A compressor is driven by an electric motor. A combined outlet intermixes airflow from the first passage and from the compressor driven by the electric motor and passes the airflow downstream to be delivered to an aircraft use.

Abstract: A liner panel within a gas turbine engine includes a perimeter rail that defines a first height from a cold side. The liner panel also includes an intermediate rail that defines a second height from the cold side, where the second height is less than the first height.

Abstract: A gas turbine engine includes a lubrication system, fuel system and thermoelectric heat exchanger adapted for selective operation in response to operational states of the gas turbine engine.

Abstract: A seal for sealing a combustor heat shield against an interior surface of a combustor shell, the seal comprising: a first sealing surface on the interior surface of the combustor shell; and a second sealing surface on a rail on an edge of a heat shield, wherein each of the first and second sealing surfaces include first and second projections defining a non-linear leakage path between the projections.

Abstract: The present invention discloses a novel apparatus and methods for controlling an air injection system for augmenting the power of a gas turbine engine, improving gas turbine engine operation, and reducing the response time necessary to meet changing demands of a power plant. Improvements in control of the air injection system include ways directed towards preheating the air injection system, including using an gas turbine components, such as an inlet bleed heat system to aid in the preheating process.

Abstract: A starter-generator module for a gas turbine engine includes an inner stator portion with an armature defining a rotation axis and an outer rotor portion disposed about the rotation axis. The outer rotor portion includes a permanent magnet and a gear teeth member. The permanent magnet is disposed about the rotation axis and the gear teeth member is defined on the outer rotor portion such that the gear teeth member transmits rotational energy to an accessory gearbox in a start mode and receives rotational energy from the accessory gearbox in a generate mode.

Abstract: A particle removal device for a gas turbine includes a suction inlet formed in one side of a region below a first vane so as to introduce a compressed air discharged from a compressor, a combusted gas generated in a combustor flowing through the first vane, an acceleration flow path for accelerating the compressed air introduced through the suction inlet so as to separate particles from the compressed air by centrifugal force, a particle collector provided at one end of the acceleration flow path so as to collect the separated particles, and a particle discharger communicating with the particle collector so as to discharge the collected particles to an outside.

Abstract: A turbofan engine according to an exemplary embodiment of this disclosure includes, among other possible things, a first spool including a first turbine; a second spool including a second turbine disposed axially forward of the first turbine; a first tower shaft engaged to the first spool; a second tower shaft engaged to the second spool; a superposition gearbox including a sun gear, a plurality of intermediate gears engaged to the sun gear and supported in a carrier and a ring gear circumscribing the intermediate gears, wherein the second tower shaft is engaged to drive the sun gear; a first clutch for selectively coupling the first tower shaft to the ring gear; a second clutch for selectively coupling the sun gear to the carrier; and an accessory gearbox driven by an output of the superposition gearbox.

Abstract: A gas turbine engine and a combustor are described herein. The combustor includes a fuel vaporizer coupled to a combustor wall, which extends into a combustion chamber. A fuel injector having a nozzle extends within a portion of the fuel vaporizer. A dome swirler is coupled to an upstream dome portion of the combustor wall. The swirler surrounds a heat shield, which may have a concaved body. The outlet end of the fuel vaporizer is disposed over the heat shield, which may be over the central zone of the heat shield, to face the heat shield. The fuel vaporizer may be coupled to the combustor wall and disposed outside the swirler. Fuel and air mixture exits the vaporizer and impinges against the heat shield and is then combined with the swirler air to become part of the primary zone recirculation.

Abstract: A gas turbine engine includes a turbine having a stage of turbine rotor blades. The gas turbine engine additionally includes a combustion section defining a cooling air passage for providing a cooling airflow to the stage of turbine rotor blades. The gas turbine engine additionally includes a fluidic nozzle assembly having a fluidic nozzle positioned in or immediately upstream of the cooling air passage of the combustion section. The fluidic nozzle defines an opening and is operable to induce cooling airflow through the opening to increase or decrease an amount of cooling air provided to the stage of turbine rotor blades to, e.g., increase an efficiency of the gas turbine engine.

Abstract: A gas turbine engine includes a buffer system that communicates a buffer supply air to a portion of the gas turbine engine. The buffer system includes a first bleed air supply having a first pressure, a second bleed air supply having a second pressure that is greater than the first pressure, and a valve that selects between the first bleed air supply and the second bleed air supply to communicate the buffer supply air to the portion of the gas turbine engine.

Abstract: A system is provided comprising: a starter air valve in fluid communication with an air turbine starter to drive motoring of a gas turbine engine responsive to a compressed air flow from a compressed air source; a manual override operably connected to the starter air valve, the manual override is operable to open the starter air valve a select percentage by moving the manual override to a detent engaged position, wherein the select percentage is operable to allow enough airflow to achieve the maximum allowed motoring speed of the gas turbine engine; and a pressure regulating bleed valve in fluid communication with the starter air valve, the pressure regulating bleed valve operable to bleed a portion of the compressed air flow to regulate a motoring speed of the gas turbine engine in response to detection of the manual override in a detent engaged position.

Abstract: The present application provides an acoustic nozzle for an inlet bleed heat system using a flow of compressor discharge air. The acoustic nozzle may include an outer casing, an acoustic attenuation medium within the outer casing, a number of exit apertures positioned in the outer casing, an air pipe in communication with the outer casing, and a reduced flow area positioned about the outer chamber and the air pipe for the flow of compressor discharge air.

Abstract: A turbine engine including a combustion chamber having an inner annular shroud and an outer annular shroud that are coaxial with each other and that are connected at their downstream ends respectively to an inner annular link wall and to an outer annular link wall, for linking respectively to an inner casing and to an outer casing. At least a first one of the inner and outer annular link walls includes at least one coolant fluid circuit extending between the radially inner and outer ends of said first annular link wall.