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Gas compressor
About: Gas compressor is a research topic. Over the lifetime, 91817 publications have been published within this topic receiving 552209 citations.
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Patent•
16 Aug 1995TL;DR: In this paper, a solid oxide fuel cell (SOFC) was combined with a turbine (104) driven by the exhaust gases of the fuel cell, and the turbine drove a generator whose power output supplemented the SOFC's power output to power the electric motor.
Abstract: Apparatus for powering an electric motor (4) comprising a solid oxide fuel cell (SOFC) (8) having a controlled fuel input (22) and a controlled oxidizer input (24). This apparatus may be combined with a turbine (104) driven by the exhaust gases of the fuel cell (8). The turbine (104) drives a generator whose power output (102) supplements the fuel cell power output (96) to power the electric motor (4). The oxidizer may be compressed by a compressor (98) driven by the turbine (104). The electric motor (4) may be a DC unipolar motor with controlled field excitation current. A controller (40') may control the fuel input (90), the compressor oxidizer input (108) or the field excitation current.
69 citations
Patent•
23 Dec 1986
TL;DR: In this article, a residential heat pump installation includes a variable speed reciprocating compressor, which is cooled by diverting the refrigerant liquid line into the closed controls compartment of the outdoor cabinet section and passing the liquid line through a block of material therein upon which the compressor speed control components are mounted.
Abstract: A residential heat pump installation includes a variable speed reciprocating compressor. The compressor speed control components, which include an inverter, are cooled by diverting the refrigerant liquid line into the closed controls compartment of the outdoor cabinet section and by passing the liquid line through a block of material therein upon which the compressor speed control components are mounted. The heat generated by the speed control components is transferred through the block of material and ultimately into the liquid refrigerant which is pumped through the liquid line by the operation of the compressor. Heat generated in the controls compartment is therefore removed from the compartment by system refrigerant in an manner which does not, to any significant degree, adversely affect the overall operation and efficiency of the system.
69 citations
TL;DR: In this article, the authors present an analytical study on heat transfer and temperature distribution for a hermetic reciprocating refrigeration compressor using the lumped thermal conductance approach, where the intricate components of a compressor were divided into 46 geometrically simplified discrete elements and each was assumed to be at a uniform temperature.
69 citations
TL;DR: The results show that the optimized blade favors a lighter weight by a thinner blade shape, attributed to a reduced separation zone and a weaken shock wave.
Abstract: In this work we perform multi-objective optimization of the NASA rotor67 transonic compressor blade. Our objectives are to maximize the stage pressure ratio as well as to minimize the compressor weight. The backbones of the optimization approach consist of a genetic algorithm, a gradient-based method, and a response surface model. The genetic algorithm is used to facilitate the multi-objective optimization and to flnd the global optima of high-dimensional problems. The gradient-based method accelerates the optimization convergence rate. The response surface model, constructed to replace the computationally expensive analysis tool, reduces the computational cost. Representative solutions are selected from the Pareto-optimal front to verify against the CFD tool. Comparing with the baseline design some optimal solutions increase the stage pressure ratio by 1.8% and decrease the weight by 5.4%. A detailed study of ∞ow structure near peak e‐ciency is presented by means of pressure distribution and streamlines inside boundary layers. Our results show that the optimized blade favors a lighter weight by a thinner blade shape. The stage pressure rise is attributed to a reduced separation zone and a weaken shock wave.
69 citations
01 Dec 2010
TL;DR: In this paper, the authors investigated the effect of the volute on the flow in a transonic, high-pressure ratio centrifugal compressor at off-design conditions, and found that the volutes severely harm aerodynamic stability of the investi- gated compressor when operating at lower than design mass flow.
Abstract: The asymmetric influence of the volute on the flow in a transonic, high-pressure ratio centrifugal compressor at off-design conditions was investigated. Fully three-dimensional vis- cous steady-state computational fluid dynamics (CFD) was applied to simulate the flow in a 4.2:1 design pressure ratio compressor for automotive application. Computed performance charac- teristics are presented for low- and high-pressure ratio operating conditions, with and without an overhung volute. The volute was found to severely harm aerodynamic stability of the investi- gated compressor when operating at lower than design mass flow. The relative narrowing effect of the volute on compressor map width increases with pressure ratio up to a 42 per cent drop in stable flow range at design speed. The inter-passage variations in performance quantities and the influence of the volute tongue region are discussed in detail. The circumferential variations of incidence angle correlate with rotational speed, which, in combination with the higher sensitivity to incidence angle at transonic inflow conditions, seems to deteriorates stability when transonic inflow conditions are reached.
69 citations