The present disclosure describes a micro gas turbine flameless heater, in which the heat is generated by burning fuel in a gas turbine engine, and the heater output air mixture is generated by transferring the heat in the gas turbine exhaust to the cold air drawn from the ambient environment. The present disclosure also describes component geometries and system layout for a gas turbine power generation unit that is designed for simple assembly, disassembly, and component replacement. The present disclosure also allows for quick removal of the rotating components of the gas turbine engine in order to reduce assembly and maintenance time. Furthermore, the present disclosure describes features that help to maintain safe operating temperatures for the bearings and structures of the gas turbine engine power turbine. Lastly, the present disclosure describes features of a fuel capture system that allow the injection of wellhead gas, which typically is a mixture of gaseous and liquid fuels, into the combustion chamber, and also describes methods of incorporating afterburners in the gas turbine engine, such that the gas turbine engine system can use wellhead gas to power equipment and reduce emissions from flaring in oil and gas applications.

The present disclosure describes a micro gas turbine flameless heater, in which the heat is generated by burning fuel in a gas turbine engine, and the heater output air mixture is generated by transferring the heat in the gas turbine exhaust to the cold air drawn from the ambient environment. The present disclosure also describes component geometries and system layout for a gas turbine power generation unit that is designed for simple assembly, disassembly, and component replacement. The present disclosure also allows for quick removal of the rotating components of the gas turbine engine in order to reduce assembly and maintenance time. Furthermore, the present disclosure describes features that help to maintain safe operating temperatures for the bearings and structures of the gas turbine engine power turbine. Lastly, the present disclosure describes features of a fuel capture system that allow the injection of wellhead gas, which typically is a mixture of gaseous and liquid fuels, into the combustion chamber, and also describes methods of incorporating afterburners in the gas turbine engine, such that the gas turbine engine system can use wellhead gas to power equipment and reduce emissions from flaring in oil and gas applications.

Systems and methods to operate an engine in a bowed rotor mitigation mode. An engine starting system includes a starter coupled to the engine and with a compressor. A conduit system communicates a portion of the compressed air from the compressor to the starter. A load control valve controls compressed air from the compressor to the starter and to other loads. A starter air valve controls compressed air through the conduit system to the starter. At least one controller: receives a start signal from the engine; determines whether to initiate a bowed rotor mitigation of the engine; operates either the load control valve or the starter air valve to move to a predetermined static position; and operates the other of the load control valve or the starter air valve to achieve a target speed of the engine.

An air turbine starter that includes a housing with a divider structure dividing the housing into a wet chamber and an air chamber. The air turbine starter further including a bearing assembly, a turbine member, a first drive shaft, and a second drive shaft connecting the turbine member with a rotating assembly. A lubricant supply portion having at least one supply inlet fluidly coupled to the wet chamber and at least one supply outlet fluidly coupled to the bearing assembly whereby lubricant from the wet chamber can be supplied to the bearing assembly.

An air turbine starter that includes a housing with a divider structure dividing the housing into a wet chamber and an air chamber. The air turbine starter further including a bearing assembly, a turbine member, a first drive shaft, and a second drive shaft connecting the turbine member with a rotating assembly. A lubricant supply portion having at least one supply inlet fluidly coupled to the wet chamber and at least one supply outlet fluidly coupled to the bearing assembly whereby lubricant from the wet chamber can be supplied to the bearing assembly.

In one aspect, the present disclosure is directed to a gas turbine starting system that includes a shaft coupling a compressor and a turbine. An annular housing extends circumferentially around the shaft such that the annular housing defines a compartment. A flange extends radially outward from the annular housing for mounting the annular housing to a stationary wall. A starter is positioned in the compartment. A collar rotatably couples to the annular housing and selectively couples to the starter. The collar includes a radially inner surface having a plurality of splines for engaging the shaft. The starter, when activated, rotates the collar, which rotates the shaft to start the gas turbine.

A starter assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a fluid-actuated starter coupled to a spool, and a controller operable to cause a reduction in torque output of the starter in response to determining that a first predefined threshold is met. The first predefined threshold relates to an engine operational condition. A method for starting a gas turbine engine is also disclosed.

A starter assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a fluid-actuated starter coupled to a spool, and a controller operable to cause a reduction in torque output of the starter in response to determining that a first predefined threshold is met. The first predefined threshold relates to an engine operational condition. A method for starting a gas turbine engine is also disclosed.

An exhaust baffle component for an aircraft starter includes a plurality of frames arranged with one another as a single component. At least one of the plurality of frames may include an attachment flange extending therefrom and defining a receiving aperture. Each frame of the plurality of frames may include one or more louvers stacked relative to one another and spaced from one another to define an air opening therebetween. The attachment flange may extend from the frame at a substantially central region of an upper portion of the frame to substantially align the receiving aperture with a starter aperture of a starter component to facilitate securement of the attachment flange to the starter component.

An exhaust baffle component for an aircraft starter includes a plurality of frames arranged with one another as a single component. At least one of the plurality of frames may include an attachment flange extending therefrom and defining a receiving aperture. Each frame of the plurality of frames may include one or more louvers stacked relative to one another and spaced from one another to define an air opening therebetween. The attachment flange may extend from the frame at a substantially central region of an upper portion of the frame to substantially align the receiving aperture with a starter aperture of a starter component to facilitate securement of the attachment flange to the starter component.