An aircraft installation of a pneumatic system of an aircraft with different compressed air sources for supplying pressurized air to air consumer equipment. Either an air bleed system, electrical compressors, or a combination thereof may perform such supplying of compressed air depending on the aircraft operation condition, for instance the flight altitude or specific flight phases. Also, a turbofan engine, and a method for supplying compressed air to air consumer equipment are disclosed.

Pumped heat energy storage systems that can be used to store and extract electrical energy. A motor/generator system is releasably coupled and decoupled via clutches from a charge mode powertrain and a generation mode powertrain depending on the operating mode of the pumped heat energy storage system.

Pumped heat energy storage systems that can be used to store and extract electrical energy. A motor/generator system is releasably coupled and decoupled via clutches from a charge mode powertrain and a generation mode powertrain depending on the operating mode of the pumped heat energy storage system.

An exhaust energy recovery system (EERS) and associated methods for an engine are disclosed. An embodiment of an EERS, for example, includes an inlet duct that is configured to divert exhaust gas from an exhaust duct of the engine into the recovery system and an outlet duct configured to return the exhaust gas to the exhaust duct downstream of the inlet duct. The recovery system is configured to heat components or fluids associated with engine to operating temperatures. The recovery system may be part of a mobile power system that is mounted to a single trailer and includes an engine and a power unit such as a high pressure pump or generator mounted to the trailer. Methods of operating and purging recovery systems are also disclosed.

A direct-fired gas turbine heater comprises a gas turbine engine, a main blower that receives cold air from the ambient, a mixing plenum that receives cold air from the main blower and hot gas from the turbine and delivers warm air, an air blower plenum that that receives cold air from the main air blower and delivers air to the mixing plenum, and an air intake plenum that receives cold air from the ambient and the air blower plenum and delivers cold air to a turbine compressor, an air intake valve, and an air starter valve. The gas turbine engine comprises the compressor that receives cold air, a fuel manifold that receives combustible fuel, a combustor that receives compressed air from the compressor and fuel from the fuel manifold, a turbine that receives hot gas from the combustor, and a shaft connecting the compressor and turbine.

A direct-fired gas turbine heater comprises a gas turbine engine, a main blower that receives cold air from the ambient, a mixing plenum that receives cold air from the main blower and hot gas from the turbine and delivers warm air, an air blower plenum that that receives cold air from the main air blower and delivers air to the mixing plenum, and an air intake plenum that receives cold air from the ambient and the air blower plenum and delivers cold air to a turbine compressor, an air intake valve, and an air starter valve. The gas turbine engine comprises the compressor that receives cold air, a fuel manifold that receives combustible fuel, a combustor that receives compressed air from the compressor and fuel from the fuel manifold, a turbine that receives hot gas from the combustor, and a shaft connecting the compressor and turbine.

A method of regulating a temperature associated with a heat exchanger assembly of a turbine engine, the method includes, in a single cycle: measuring the temperature of an air stream at the outlet from a heat exchanger; receiving a setpoint temperature for the air stream at the outlet from the heat exchanger; estimating a theoretical temperature for the air stream at the outlet from the heat exchanger as a function of an estimate of the shutter position of a controlled valve bleeding off a cooling air stream for the heat exchanger; determining a correction current from the difference between the measured temperature and the theoretical temperature; and determining a control current for the shutter from the difference between the measured temperature and the setpoint temperature and the correction current determined during the preceding cycle, the shutter position being determined from the control and correction currents determined during the preceding cycle.

A large frame heavy duty industrial gas turbine engine that can produce twice the power as a conventional single spool industrial engine, and can operate at full power during a hot day. The industrial engine includes a high spool that directly drives an electric generator at a synchronous speed of the electric power grid, a low spool with a low pressure turbine that drives a low pressure compressor from the exhaust gas from the high pressure turbine, where the low pressure compressor supplies compressed air to the high pressure compressor. Variable inlet guide vane assemblies are used in the low pressure turbine and the low pressure compressor so that the high spool can operate at full power even during a hot day. The low spool is designed to operate at a higher speed than at the normal temperature conditions so that a high mass flow can be produced for the high spool during the hot day conditions.

A method and apparatus for supplying air to a precooler. Air flow is created through a fan duct in an engine system. A first portion of the air flow is directed into a first inlet of an inlet system to feed a first half of the precooler. A second portion of the air flow is directed through the fan duct into a second inlet of the inlet system to feed a second half of the precooler.

A method and apparatus for supplying air to a precooler. Air flow is created through a fan duct in an engine system. A first portion of the air flow is directed into a first inlet of an inlet system to feed a first half of the precooler. A second portion of the air flow is directed through the fan duct into a second inlet of the inlet system to feed a second half of the precooler.