Provided are a fluid circulation system and a method for operating same, a computer-readable medium, and a controller. The fluid circulation system comprises: a scroll expander, and an external fluid circulation path, which comprises a high-pressure fluid pipe and a low-pressure fluid pipe. The operation method comprises the following steps: before fluid is supplied to the scroll expander, making the fluid pressure in the high-pressure fluid pipe higher than the fluid pressure in the low-pressure fluid pipe by a pre-determined pressure difference; and after the pre-determined pressure difference is realized, starting the scroll expander and supplying fluid to the scroll expander. According to the present disclosure, the technical problem of a scroll expander being unable to be normally started and work can be avoided, and the invention is simple, practical, convenient, and easily implemented.

A compact energy cycle construction that operates as or in accordance with a Rankine, Organic Rankine, Heat Pump, or Combined Organic Rankine and Heat Pump Cycle, comprising a compact housing of a generally cylindrical form with some combination of a scroll type expander, pump, and compressor disposed therein to share a common shaft with a motor or generator and to form an integrated system, with the working fluid of the system circulating within the housing as a torus along the common shaft and toroidally within the housing as the system operates.

The present teachings generally include an energy recovery device with heat dissipation mechanisms. The energy recovery device can include a main housing, rotors disposed in the main housing, rotor shafts associated with the rotors, and a sub-housing. The sub-housing can have an engaging surface that faces and is spaced apart from the first receiving surface of the main housing with a first gap when the first sub-housing is attached to the main housing.

A compound engine system including a Wankel engine having a recess defined in the peripheral wall of the rotor in each of the three rotating chambers, the recess having a volume of more than 5% of the displacement volume of the chambers. The expansion in the turbine section compensates for the relatively low expansion ratio of the rotary engine.

Provided are a fluid circulation system and a method for operating same, a computer-readable medium, and a controller. The fluid circulation system comprises: a scroll expander, and an external fluid circulation path, which comprises a high-pressure fluid pipe and a low-pressure fluid pipe. The operation method comprises the following steps: before fluid is supplied to the scroll expander, making the fluid pressure in the high-pressure fluid pipe higher than the fluid pressure in the low-pressure fluid pipe by a pre-determined pressure difference; and after the pre-determined pressure difference is realized, starting the scroll expander and supplying fluid to the scroll expander. According to the present disclosure, the technical problem of a scroll expander being unable to be normally started and work can be avoided, and the invention is simple, practical, convenient, and easily implemented.

A compound engine system includes a rotary engine with rotating chambers, a compressor section in successive communication with the rotating chambers, and a turbine section in successive communication with the rotating chambers. The turbine section has an output shaft. The output shaft and the engine shaft are drivingly engaged to each other and wherein the turbine section has a power output corresponding to from 20% to 35% of a total power output of the compound engine system. A method of compounding power in a compound engine system is also discussed.

A method of operating an aircraft engine of an aircraft, the aircraft engine having a common-rail fuel injection system for injecting fuel into a combustion chamber of the aircraft engine, including: pressurizing fuel for circulation through the common-rail injection system; circulating a portion of the pressurized fuel through a motive flow inlet of an ejector pump; and entraining a flow through the ejector pump with the portion of the pressurized fuel circulating through the motive flow inlet.

This patent discloses thrust vectoring ignition chamber engine. Thrust vectoring ignition chamber used in this engine is an annular cylinder having nozzles mounted in a way such that during fuel suction phase they are sealed and during ignition of fuel they are unsealed so that hot jets of ignited fuel escaping through nozzles cause coupled rotatory motion on the ignition chamber. Engine uses cam operated suitably modified 3-screw compressor for suction and compression of fuel and therefore do not require piston mechanism. Flywheel mounted on extension of ignition chamber functions as output of the engine. Each half rotation of flywheel completes three phases namely fuel/air suction, compression and combustion. Thus this engine fires for every half revolution and therefore can give improved power boost.

Compressor and a refrigeration cycle device, relating to the field of refrigeration technology. The compressor includes a housing, and a drive assembly, a compression assembly and an expansion assembly which are provided in the housing; the compression assembly is connected to and driven by the drive assembly, and is configured to perform multi-stage compression on a refrigerant under drive of the drive assembly; the expansion assembly is connected to the drive assembly and is configured to expand the refrigerant compressed by the compression assembly. A refrigeration cycle device includes the compressor.

A method of operating an aircraft engine of an aircraft, the aircraft engine having a common-rail fuel injection system for injecting fuel into a combustion chamber of the aircraft engine, including: pressurizing fuel for circulation through the common-rail injection system; circulating a portion of the pressurized fuel through a motive flow inlet of an ejector pump; and entraining a flow through the ejector pump with the portion of the pressurized fuel circulating through the motive flow inlet.