Gas compressor

About: Gas compressor is a research topic. Over the lifetime, 91817 publications have been published within this topic receiving 552209 citations.

Airconditioner having selectively operated condenser bypass control

Abstract: A heater core is connected with an engine to receive a hot engine-coolant, which operates as a main heater. An evaporator in a refrigerating cycle operates as an auxiliary heater. A condenser is connected to an outlet of the compressor, and the evaporator is connected to an inlet of the compressor. A bypass conduit is provided, one end of which is connected to the outlet side of the compressor and another end of which is connected to an inlet side of the evaporator. A expansion valve is disposed in the bypass conduit. In heating stage, the compressed hot refrigerant discharged from the compressor flows into the bypass conduit. The refrigerant is expanded by the expansion valve and radiates the heat in the evaporator.

Research on the Steady Operation Optimization Model of Natural Gas Pipeline Considering the Combined Operation of Air Coolers and Compressors

Abstract: Based on the mutual coupling effect among the compressor, the air cooler and pipes in the system of natural gas pipeline, innovatively with the goal of minimum energy consumption, this paper established a combined operation optimization model of the air cooler and compressor through the optimization of the switching scheme of compressors and air coolers, which can greatly reduce the production energy consumption of the pipeline system. Moreover, when the air temperature is taken as an optimization variable, the most proper temperature to start the air cooler of each compressor station can be worked out to guide the optimized operation of the pipeline, which is of high value for promotion and application. The case analysis of west-east natural gas pipeline II showed that among genetic algorithm (GA), particle swarm optimization (PSO), and simulated annealing (SA) algorithm that are used to solve the optimization model, the genetic algorithm is the fastest, and the simulated annealing algorithm the slowest, but the optimization results of the simulated annealing algorithm is the best, in which the reduced production energy consumption accounted for 33.77%, testifying the practicability and creativity of the optimization model.

Multiple stage supercharging system

Abstract: A multiple stage supercharging system is disclosed suitable for both two-stroke cycle and four-stroke cycle internal combustion engines Ambient air, which is propelled by the forward velocity of the engine, enters an air cleaner housing (11) through an air filter The air cleaner housing (11) attaches to the air intake (32) of a centrifugal compressor (12) The centrifugal compressor (12) mounts directly to the magnetic flywheel on the crankshaft of the engine The centrifugal compressor wheel (22) pressurizes the ambient air for use in the combustion process The outlet of the centrifugal compressor housing mates with a secondary plenum chamber (17) The outlet of the secondary plenum chamber (17) mates with a dc motor driven axial compressor (28) The axial compressor (28) operates on current derived from a motor driven alternator (38) The outlet of the axial compressor connects to a primary plenum chamber (18) which connects to the air intake snorkel on the carburetor A pressure equalization tube (19) extends from the primary plenum chamber to the carburetor bowl to allow for consistent flow of the air/fuel mixture to the crankcase The system provides for multiple compressors to generate layers of additive pressure for supercharging an internal combustion engine The system provides air pressure to boost the power output of the engine across the entire rpm band by utilizing the centrifugal compressor (12) and the axial compressor (28) at low speeds and by utilizing forward air velocity air intake pressure plus the centrifugal and axial compressors at high speeds

Modeling and Simulation of a Gas Turbine Engine for Power Generation

Abstract: The gas turbine engine is a complex assembly of a variety of components that are designed on the basis of aerothermodynamic laws. The design and operation theories of these individual components are complicated. The complexity of aerothermodynamic analysis makes it impossible to mathematically solve the optimization equations involved in various gas turbine cycles. When gas turbine engines were designed during the last century, the need to evaluate the engines performance at both design point and off design conditions became apparent. Manufacturers and designers of gas turbine engines became aware that some tools were needed to predict the performance of gas turbine engines especially at off design conditions where its performance was significantly affected by the load and the operating conditions. Also it was expected that these tools would help in predicting the performance of individual components, such as compressors, turbines, combustion chambers, etc. At the early stage of gas turbine developments, experimental tests of prototypes of either the whole engine or its main components were the only method available to determine the performance of either the engine or of the components. However, this procedure was not only costly, but also time consuming. Therefore, mathematical modelling using computational techniques were considered to be the most economical solution. The first part of this paper presents a discussion about the gas turbine modeling approach. The second part includes the gas turbine component matching between the compressor and the turbine which can be met by superimposing the turbine performance characteristics on the compressor performance characteristics with suitable transformation of the coordinates. The last part includes the gas turbine computer simulation program and its philosophy. The computer program presented in the current work basically satisfies the matching conditions analytically between the various gas turbine components to produce the equilibrium running line. The computer program used to determine the following: the operating range (envelope) and running line of the matched components, the proximity of the operating points to the compressor surge line, and the proximity of the operating points at the allowable maximum turbine inlet temperature. Most importantly, it can be concluded from the output whether the gas turbine engine is operating in a region of adequate compressor and turbine efficiency. Matching technique proposed in the current work used to develop a computer simulation program, which can be served as a valuable tool for investigating the performance of the gas turbine at off-design conditions. Also, this investigation can help in designing an efficient control system for the gas turbine engine of a particular application including being a part of power generation plant.