摘要:

The performance of a turbocompressor comprised of a large number of mechanically independent compressor and turbine stages is considered. Examination of the equilibrium conditions of any stage shows its performance, for a given design, to be dependent on four variables and hence the performance of the complete unit is also dependent on the same four variables. Exact arithmetical calculation would be possible, but very tedious. In order to render computation easier, the conception of reflected conditions is introduced. Physically this implies independence of each stage, in some respects, from its neighbors. The assumption is likely to be in error least for intermediate stages, and most for the first and last stages. Methods of expressing the aerodynamic performance of the blades of the compressor and turbine stages are introduced to render calculation easier. Some calculated performance figures are compared with experimental values and show by their reasonable agreement that the assumptions used are valid. The methods can be applied to other types of complex turbocompressor units by suitable modification of procedure and details.

ISSN:1923-4287    

DOI:10.1139/cjr49f-029

出版商:NRC Research Press    

年代:1949

数据来源: NRC

摘要:

not available

ISSN:1923-4287    

DOI:10.1139/cjr49f-030

出版商:NRC Research Press    

年代:1949

数据来源: NRC