A bladeless conical radial rotary machine method and system are disclosed. Turbo-machinery and methods are disclosed for a bladeless conical radial rotary machine wherein fluid is directed axially within the pump body to produce an axial output. The rotor comprises a plurality of spaced apart conical elements. The fluid is smoothly directed to any number of subsequent boundary layer pumping stages which are axially positioned with respect to each other. The fluid is smoothly directed to any number of subsequent boundary layer pumping stages which are axially positioned with respect to each other. A coupling between pumping stages is disclosed.

A gas turbine engine includes a first shaft coupled to a first turbine and a first compressor, a second shaft coupled to a second turbine and a second compressor, and a third shaft coupled to a third turbine and a fan assembly. The turbine engine includes a heat rejection heat exchanger configured to reject heat from a closed loop system with air passed from the fan assembly, and a combustor positioned to receive compressed air from the second compressor as a core stream. The closed-loop system includes the first, second, and third turbines and the first compressor and receives energy input from the combustor.

A method of identifying the phase composition and/or changes in the phase composition of a fluid flowing through a turbomachine includes monitoring changes in at least one electrical parameter associated with operation of the turbomachine, and employing a known correlation between phase composition and or phase composition changes, and changes in the electrical parameter(s) to associate the monitored changes with changes in the actual phase composition of the fluid.

The present invention describes a jet engine with a device for spraying oil into an air-oil volume flow guided inside a flow cross-section limited by a wall area. The air-oil volume flow is guidable through an oil separator in order to separate the oil. In accordance with the invention, the oil can be sprayed into the air-oil volume flow in the area of the device via an outlet area rigidly connected to the wall area.

A gas turbine engine includes a first shaft coupled to a first turbine and a first compressor, a second shaft coupled to a second turbine and a second compressor, and a third shaft coupled to a third turbine and a fan assembly. The turbine engine includes a heat rejection heat exchanger configured to reject heat from a closed loop system with air passed from the fan assembly, and a combustor positioned to receive compressed air from the second compressor as a core stream. The closed-loop system includes the first, second, and third turbines and the first compressor and receives energy input from the combustor.

An object of the present invention is to provide a method and a system for implementing the method so as to alleviate the disadvantages of a reciprocating combustion engine and gas turbine in electric energy production. The invention is based on the idea of arranging a combustion chamber outside a gas turbine and providing compressed air to the combustion chamber in order to carry out a combustion process supplemented with high pressure steam pulses.

A centrifugal compressor for processing a wet gas. The centrifugal compressor includes: a casing; and least one compressor stage comprising at least one impeller rotatingly arranged in the casing and provided with an impeller hub and a plurality of impeller blades, each impeller blade having a suction side and a pressure side. The at least one compressor stage comprises at least one droplet breaking arrangement configured for promoting breakup of liquid droplets flowing through the compressor stage.

A bladeless conical radial rotary machine method and system are disclosed. Turbo-machinery and methods are disclosed for a bladeless conical radial rotary machine wherein fluid is directed axially within the pump body to produce an axial output. The rotor comprises a plurality of spaced apart conical elements. The fluid is smoothly directed to any number of subsequent boundary layer pumping stages which are axially positioned with respect to each other. The fluid is smoothly directed to any number of subsequent boundary layer pumping stages which are axially positioned with respect to each other. A coupling between pumping stages is disclosed.

LNG cold power generator includes: a working fluid including carbon dioxide and ethane; a pump; an evaporator; a turbine; and a condenser. A molar ratio of the carbon dioxide and the ethane is 8595:15:0.5. The working fluid is used in a closed Rankine cycle. A supply pressure of supplied LNG is adjusted to a pressure at which it becomes a saturated liquid. A temperature at an outlet of the condenser is adjusted to a saturated vapor temperature of LNG. A pressure at an outlet of the pump is adjusted to a critical pressure of a mixed working fluid. The cycle includes two turbines and a heater provided therebetween. The heater heats the working fluid to prevent condensation thereof.

A wet-gas centrifugal compressor is disclosed. The compressor comprises a compressor casing and at least one impeller arranged in the compressor casing for rotation around a rotation axis. A stationary diffuser is arranged in the compressor casing and extends around the impeller. The diffuser has a curved end portion with a radially inner curved wall and a radially outer curved wall. A plurality of dry-gas extraction holes is provided, ending at a plurality of respective inlet ports arranged around the rotation axis and on the inner curved wall of the curved end portion of the diffuser. Each dry-gas extraction hole extends from the respective inlet port towards the rotation axis and is inclined over a radial direction, such that each dry-gas extraction hole is oriented in a counter-flow direction with respect to a direction of the gas flow in the curved end portion of the diffuser.