Systems and generating power in an organic Rankine cycle (ORC) operation to supply electrical power. In embodiments, an inlet temperature of a flow of gas from a source to an ORC unit may be determined. The source may connect to a main pipeline. The main pipeline may connect to a supply pipeline. The supply pipeline may connect to the ORC unit thereby to allow gas to flow from the source to the ORC unit. Heat from the flow of gas may cause the ORC unit to generate electrical power. The outlet temperature of the flow of the gas from the ORC unit to a return pipe may be determined. A bypass valve, positioned on a bypass pipeline connecting the supply pipeline to the return pipeline, may be adjusted to a position sufficient to maintain temperature of the flow of gas above a threshold based on the inlet and outlet temperature.

A method for starting and stopping a gas turbine in a combined cycle power plant, wherein the gas turbine includes a compressor having adjustable guide vanes and the gas turbine power can also be controlled by opening the guide vanes. When the gas turbine is started, it is driven up to a base load or up to an emission-compliant load point, and the guide vanes are opened before the base load or the emission-compliant load point is reached.

The invention relates to a method (E) for detecting the ignition of a turbine engine combustion chamber, the method (E) comprising the steps of: receiving (E11) a first measurement of the exhaust gas temperature downstream from the combustion chamber, before an attempt to ignite said combustion chamber; receiving (E12) a temperature threshold; receiving (E13) a secondary detection criterion; updating (E14) the received temperature threshold as a function of the secondary detection criterion received; receiving (E15) a second measurement of the exhaust gas temperature, after the attempt to ignite the combustion chamber; comparing (E16) the updated temperature threshold with the difference between the first and second exhaust gas temperature measurements; and determining (E17) the state of ignition of the combustion chamber.

A turbomachine includes a shroud and a rotor, which includes first and second blades. A first blade tip and a second blade tip respectively include a base and a first layer. The second blade tip also includes an abrasive second layer layered over the respective first layer. The first layer has a lower material hardness than the shroud. The second layer has a lower thermal stability than the shroud and the first layer. The rotor performs a grind operation and, subsequently, a post-grind operation. The second layer, in the grind operation, contacts and removes material from the shroud, and wears away, thereby revealing the first layer of the second blade tip for the post-grind operation. The first layer of the first blade tip is spaced apart with at least some radial clearance from the shroud in the grind and post-grind operations.

Embodiments of the disclosure provide a method for controlling steam pressure within a turbine component. The method includes calculating a predicted stress on a rotor of the turbine component based on a predicted steam flow with the inlet valve in a minimum load position, a rotor surface temperature, and an inlet steam temperature, and determining whether the predicted stress exceeds a threshold. If the predicted stress exceeds the threshold, the inlet valve adjusts to a warming position. When steam in the discharge passage reaches a target pressure, the exhaust valve partially closes while maintaining the warming position of the inlet valve. If a safety parameter of the turbine component violates a boundary, the exhaust valve partially opens while maintaining the warming position of the inlet valve. When the predicted stress does not exceed the threshold, the inlet valve opens to at least the minimum load position.

An air turbine starter for starting an engine includes a starter housing defining an inlet, an outlet, and a flow path extending between the inlet and the outlet. A turbine section is located within the starter housing and includes a turbine member having a central disk and a set of airfoils spaced circumferentially about the central disk, as well as a sealing structure located within the starter housing.

An air turbine starter for starting an engine includes a starter housing defining an inlet, an outlet, and a flow path extending between the inlet and the outlet. A turbine section is located within the starter housing and includes a turbine member having a central disk and a set of airfoils spaced circumferentially about the central disk, as well as a sealing structure located within the starter housing.

A method for operating a hybrid-electric propulsion system of an aircraft is provided. The hybrid-electric propulsion system includes a gas turbine engine having a high pressure system, a low pressure system, and an electric machine coupled to one of the high pressure system or low pressure system. The method includes receiving data indicative of an actual or anticipated in-flight shutdown of the gas turbine engine; and adding power to the gas turbine engine through the electric machine in response to receiving data indicative of the actual or anticipated in-flight shutdown of the gas turbine engine.

Embodiments of a power generation system and methods to be used in conjunction with a high-powered turbine engine are disclosed. The power generation system includes a turbine engine having an exhaust diffuser section installed on the exhaust duct of the turbine engine and a turbine engine exhaust stack assembly connected to the turbine engine exhaust diffuser section. An embodiment further includes thermo-electric generator (TEGs) sub-assemblies connected to the turbine engine exhaust stack assembly. In other embodiments electrical storage devices such as batteries are used.

Embodiments of a power generation system and methods to be used in conjunction with a high-powered turbine engine are disclosed. The power generation system includes a turbine engine having an exhaust diffuser section installed on the exhaust duct of the turbine engine and a turbine engine exhaust stack assembly connected to the turbine engine exhaust diffuser section. An embodiment further includes thermo-electric generator (TEGs) sub-assemblies connected to the turbine engine exhaust stack assembly. In other embodiments electrical storage devices such as batteries are used.