Abstract: A method of assembling a mobile electric power generation system comprises providing a generator trailer having an electric generator, a gas turbine trailer having a gas turbine, an exhaust trailer having an exhaust device, and an air filter and ventilation trailer having an air inlet device. The method includes positioning each of the generator trailer, the gas turbine trailer, the exhaust trailer, and the air filter and ventilation trailer at a job site such that the generator trailer and the gas turbine trailer are in an end-to-end configuration. The method comprises coupling each of the generator trailer, the exhaust trailer, and the air filter and ventilation trailer to the gas turbine trailer in an operational mode for generating power and decoupling each of the generator trailer, the exhaust trailer, and the air filter and ventilation trailer from the gas turbine trailer in a transport mode for transport.

Abstract: Methods and systems for controlling a bleed-off valve of a gas turbine engine are described. The method comprises maintaining a first bleed-off valve associated with a first compressor of the gas turbine engine at least partially open upon detection of an unintended engine disturbance causing a drop in pressure of a combustion chamber of the engine; monitoring a rotor acceleration of the first compressor; and controlling closure of the first bleed-off valve when the rotor acceleration of the first compressor reaches a first threshold for a first duration.

Abstract: A combustor of an embodiment includes: a combustor casing; a combustor liner which is provided in the combustor casing and combusts a fuel and an oxidant to produce a combustion gas; a pipe-shaped member provided to penetrate the combustor casing and the combustor liner; a heat-resistant glass which is provided on the combustor casing side in the pipe-shaped member and closes the pipe-shaped member; a laser light supply mechanism which irradiates an interior of the combustor liner through the heat-resistant glass and an interior of the pipe-shaped member with a laser light; and a contact prevention mechanism which prevents a combustion gas in the combustor liner from coming into contact with the heat-resistant glass.

Abstract: A propulsor section includes a propulsor having a plurality of blades rotatable about an engine longitudinal axis. A compressor section includes a low pressure compressor and a high pressure compressor. A turbine section includes a low pressure turbine that drives the propulsor through an epicyclic gear arrangement, and includes a second turbine that drives the high pressure compressor. A power ratio is provided by the combination of a first power input of the low pressure compressor and a second power input of the high pressure compressor. The power ratio is defined by the second power input divided by the first power input. The power ratio is equal to, or greater than, 1.0 and less than, or equal to, 1.4.

Abstract: A gas turbine engine includes a shaft and a hub supported by the shaft. A housing includes an inlet and an intermediate case that respectively provide an inlet and an intermediate case flow path. A rotor is connected to the hub and supports a compressor section arranged axially between the inlet and the intermediate case flow paths. A compressor section inlet has a radially inner boundary that is spaced a second radial distance from the rotational axis different from the first radial distance. First and second bearings support the shaft relative to the intermediate case and the inlet case, respectively. An inner race of the first bearing and an inner race of the second bearing engage and rotate with the hub. A fan shaft is drivingly connected to a fan having fan blades. A gear system is connected to the fan shaft and driven through a flex shaft.

Abstract: Systems and methods of operating systems are provided. For example, a system comprises a fuel cooling loop including a cold fuel flowpath having a fuel flowing therethrough, a fuel cooler heat exchanger for cooling the fuel in fluid communication with the cold fuel flowpath, and a cold fuel tank disposed along the cold fuel flowpath for accumulating at least a portion of the cooled fuel. The system further comprises a fuel heating loop including a hot fuel flowpath for a flow of the fuel, a fuel heater heat exchanger for heating the fuel in fluid communication with the hot fuel flowpath, and a hot fuel tank disposed along the hot fuel flowpath for accumulating at least a portion of the heated fuel. The fuel cooling loop is coupled to the fuel heating loop such that the fuel circulates through both the fuel cooling loop and the fuel heating loop.

Abstract: A system of a hybrid aircraft includes a first gas turbine engine including a fan, a high speed spool, and a low spool motor configured to drive rotation of the fan. The system also includes a second gas turbine engine and a controller. The controller is operable to determine an operating mode of the hybrid aircraft, control the low spool motor to drive rotation of the fan of the first gas turbine engine responsive to a thrust command while the second gas turbine engine is driven by commanding fuel combustion based on the operating mode, and accelerate the high speed spool of the first gas turbine engine and command fuel combustion at the first gas turbine engine based on a transition of the operating mode to perform a starting operation of the first gas turbine engine.

Abstract: A system includes a gas turbine engine having a low speed spool, a high speed spool, and a combustor. The system also includes a low spool motor configured to augment rotational power of the low speed spool. The system further includes a controller configured to cause fuel flow. The controller is operable to control the low spool motor to drive rotation of the low speed spool responsive to a thrust command while the controller does not command fuel flow to the combustor.

Abstract: Pressure regulators together with associated methods and systems are provided. An embodiment of a pressure regulator includes a chamber having an inlet port for receiving a fluid and an outlet port for delivering the fluid at a regulated pressure. The pressure regulator includes a diaphragm defining at least part of the chamber, and the diaphragm defining a first orifice therethrough. The pressure regulator includes a spring configured to interact with the diaphragm. The pressure regulator includes an interface operatively disposed between the spring and the diaphragm. The interface includes a contact surface for contacting the diaphragm, and the contact surface is convex toward the diaphragm. The interface defines a second orifice therethrough that is in fluid communication with the first orifice in the diaphragm. The first and second orifices define a relief port for venting the chamber to an ambient environment external to the chamber.

Abstract: A gas turbine engine includes a core cowl and a core contained within the core cowl. The core includes a compressor in fluid communication with a downstream combustor and a downstream turbine, the compressor including a compressor bleed port, wherein an undercowl space is defined between the core cowl and the core. The gas turbine engine further includes a cooling duct disposed at least partially in the undercowl space and having an inlet and an outlet, wherein the cooling duct is in fluid communication with a source of cooling air and is further in fluid communication with the compressor bleed port; a valve assembly including at least one valve disposed in the cooling duct; and a cooling blower disposed within the engine and operable to move an air flow from the inlet of the cooling duct towards the outlet of the cooling duct and through the compressor bleed port.

Abstract: A gas turbine engine (10) includes a compressor section, a turbine section, and an accessory gearbox (100). A turning unit (200) for the gas turbine engine includes an output assembly (204) configured to be mechanically coupled to the gas turbine engine, and an electric motor (202). The electric motor is operable to rotate, through the output assembly, one or more components of the compressor section or the turbine section at a rotational speed less than about fifty revolutions per minute during a shut-down condition of the gas turbine engine.

Abstract: An embodiment of a combustor for a gas turbine engine includes a combustor case, a combustor liner disposed within the combustor case, a fuel nozzle at an upstream end of the combustor liner, a torch igniter within the combustor case, and a removable fuel injector. The torch igniter includes a combustion chamber, a cap configured to receive a removable fuel injector and a surface igniter, a tip, an annular igniter wall extending from the cap to the tip and defining a radial extent of the combustion chamber, a structural wall coaxial with and surrounding the igniter wall, and an outlet passage within the tip which fluidly connects the combustion chamber to the combustor. The removable fuel injector extends through a fuel injector opening of the combustor case. The diameter of the fuel injector opening is wider than a fuel injector diameter of the removable fuel injector.

Abstract: Fuel systems of gas turbine engines of aircraft, and associated methods are provided. The fuel systems and methods can permit reverse purging of one or more fuel manifolds of a gas turbine engine to prevent coking in some modes of operation. A fuel system includes first and second fuel manifolds fluidly connectable to a combustor of the gas turbine engine. A valve is operatively disposed between the second fuel manifold and a fuel supply line for controlling fuel supply to the second fuel manifold. A reservoir includes a movable piston disposed therein and dividing the reservoir into a first chamber and a second chamber. The first chamber is fluidly connectable to the fuel supply line or to a fuel purge line via the valve. The second chamber is in fluid communication with the second fuel manifold to receive residual fuel from the second fuel manifold.

Abstract: A hybrid electric gas turbine engine includes a fan section having a fan, a turbine section having a turbine drivably connected to the fan through a main shaft that extends along a central longitudinal axis, a gas generating core extending along a first axis that is radially offset from the central longitudinal axis, and an electric motor drivably connected to the main shaft, wherein the electric motor is colinear with the main shaft.

Abstract: An assembly is provided for an aircraft propulsion system. This assembly includes a nacelle inner structure and a deflection limiter. The nacelle inner structure includes an internal compartment and a cowl. The internal compartment is configured to house a core of a gas turbine engine. The cowl is configured to form an outer radial periphery of the internal compartment. The cowl is also configured to form an outer radial periphery of a compartment exhaust to the internal compartment at an aft end of the cowl. The deflection limiter is attached to the cowl. The deflection limiter is configured to limit radial outward movement of the cowl.

Abstract: Fuel injectors having a fuel-air heat exchange system and methods thereof for use in a gas turbine engine. The fuel-air heat exchanger allows heat transfer between a flow of cooling air used to cool components of the engine and a flow of fuel used to drive the engine to transfer heat to the flow of fuel and cool the cooling air.

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: An engine driven environmental control system (ECS) air circuit includes a gas turbine engine having a compressor section. The compressor section includes a plurality of compressor bleeds. A selection valve selectively connects each of said bleeds to an input of an intercooler. A second valve is configured to selectively connect an output of said intercooler to at least one auxiliary compressor. The output of each of the at least one auxiliary compressors is connected to an ECS air input.

Abstract: Steam production apparatuses are provided. The apparatuses can include at least two compartments that are mechanically engaged. Processes for the production of steam are also provided. The processes can include providing liquid water to a reactive material within a first compartment to generate steam within the first compartment; transferring at least some of the steam to a second compartment that is mechanically engaged with the first compartment; and exposing the steam from the first compartment to material within the second compartment that extends when exposed to the steam, the extending of the material reducing the volume of the first compartment.

Abstract: At a well site, equipment will need a power source, such as a gas turbine, to operate. As the gas turbine operates, wasted energy in the form of heat is produced as a result of the efficiency of the gas turbine. With regards to the present disclosure, the heat may be used for operations and treatments at the well site. An embodiment of the present disclosure is a heat recovery system, comprising a gas turbine; a first heat exchanger, wherein the first heat exchanger is a finned-tube heat exchanger; and a second heat exchanger, wherein the second heat exchanger is a tube and shell heat exchanger, wherein the first heat exchanger is disposed in the flow path of an exhaust stream of the gas turbine, wherein the first heat exchanger is fluidly coupled to the second heat exchanger.