A hybrid propulsion system includes a wave rotor combustion engine operating in parallel with an electrical motor-generator element. The motor-generator element is coupled to the turbine shaft to selectively drive or be driven by the turbine shaft. In one mode of operation, the motor of the motor generator element is powered by a battery to provide rotational energy to the turbine shaft. In another mode of operation, the wave rotor combustion engine drives the generator to recharge the battery. The wave rotor combustion engine may be further directly coupled to auxiliary components without a gearbox to drive the components at substantially the same speed as the turbine shaft. The turbine rotor of the combustion engine includes a plurality of chambers defined by circumferentially spaced curved vanes that improves specific fuel consumption for the engine.

Methods and systems for low emission power generation in combined cycle power plants are provided. One system includes a gas turbine system that stoichiometrically combusts a fuel and an oxidant in the presence of a compressed recycle stream to provide mechanical power and a gaseous exhaust. The compressed recycle stream acts as a diluent to moderate the temperature of the combustion process. A boost compressor can boost the pressure of the gaseous exhaust before being compressed into the compressed recycle stream. A purge stream is tapped off from the compressed recycle stream and directed to a C0.sub.2 separator which discharges C0.sub.2 and a nitrogen-rich gas which can be expanded in a gas expander to generate additional mechanical power.

Methods and systems for low emission power generation in combined cycle power plants are provided. One system includes a gas turbine system that stoichiometrically combusts a fuel and an oxidant in the presence of a compressed recycle stream to provide mechanical power and a gaseous exhaust. The compressed recycle stream acts as a diluent to moderate the temperature of the combustion process. A boost compressor can boost the pressure of the gaseous exhaust before being compressed into the compressed recycle stream. A purge stream is tapped off from the compressed recycle stream and directed to a C0.sub.2 separator which discharges C0.sub.2 and a nitrogen-rich gas which can be expanded in a gas expander to generate additional mechanical power.

An enhanced pressure-wave supercharger for a combustion engine utilizes a superior pressure wave process cycle design. The design utilizes a select final portion of the compressed gas stream exiting the rotor, and supplies it to a subsequent inlet port ahead of and prior to the introduction into the rotor of the aspirated air to be compressed. Work is extracted within the rotor from this gas stream and transferred into rotational energy of the rotor through using a portion the available momentum of the compressed gas via incidence on the rotor webs to turn the rotor by means of conventional turbomachinery principles.

A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor including: a forward liner segment; and an aft liner segment disposed downstream from the forward liner segment relative to a direction of flow through the combustor, the forward and aft liner segments at least partially defining a combustion chamber, wherein the forward and aft liner segments are coupled together at a moveable interface.

A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor including: a forward liner segment; and an aft liner segment disposed downstream from the forward liner segment relative to a direction of flow through the combustor, the forward and aft liner segments at least partially defining a combustion chamber, wherein the forward and aft liner segments are coupled together at a moveable interface.

A lip seal-type shaft seal device that exhibits no leakage when at rest; operates under fluid lubrication and prevents leakage when rotating, including during initial rotation; and enables a balance between seal integrity and lubrication is provided. The device includes a plurality of discontinuous pumping areas for generating pumping action via the relative rotational sliding of a lip seal and a rotating member is formed in the circumferential direction on the outer circumferential surface of the rotating member. The plurality of pumping areas is provided with suction portion of pumping areas operating in a direction in which a sealed fluid is drawn in and discharge portion of pumping areas operating in a direction in which the sealed fluid is expelled. A lip of the lip of the lip seal extends in an axial direction towards an atmosphere side, leaving part of the pumping areas uncovered on a sealed fluid side.

A lip seal-type shaft seal device that exhibits no leakage when at rest; operates under fluid lubrication and prevents leakage when rotating, including during initial rotation; and enables a balance between seal integrity and lubrication is provided. The device includes a plurality of discontinuous pumping areas for generating pumping action via the relative rotational sliding of a lip seal and a rotating member is formed in the circumferential direction on the outer circumferential surface of the rotating member. The plurality of pumping areas is provided with suction portion of pumping areas operating in a direction in which a sealed fluid is drawn in and discharge portion of pumping areas operating in a direction in which the sealed fluid is expelled. A lip of the lip of the lip seal extends in an axial direction towards an atmosphere side, leaving part of the pumping areas uncovered on a sealed fluid side.

A stator assembly is provided and includes a stator element and a radial height adjustment mechanism. The stator assembly includes an inboard portion which establishes a primary clearance with rotor elements and exhibits a measurable parameter corresponding to the primary clearance and an outboard portion integrally formed with the inboard portion. The radial height adjustment mechanism is coupled with the outboard portion and configured to be operable, based on the measurable parameter, to adjust a radial height of the stator element and in turn to adjust the primary clearance.

A method for controlling a gas turbine, wherein measurement signal values are measured at different times, namely at least a first time and a second time, wherein the first time lies before the second time and wherein attenuated signal values are generated from the measurement signal values by smoothing the measured measurement signal values by means of a attenuation factor, wherein a different attenuation factor is used depending on the difference of the measurement signal value at the second time and the attenuated signal value at the first time.