Calculations for axial compressor blading with uniform inlet enthalpy and radial enthalpy gradient
MetadataShow full item record
A computer program was used to calculate the radial distribution of flow parameters in an axial compressor stage designed to have a symmetrical velocity diagram at the mean radius and particular variations of reaction from hub to tip. Uniform energy addition was assumed to occur in the rotor. Both cases of uniform enthalpy and uniform radial enthalpy gradient at the entrance to the stage were considered. Advantages were found in the selection of fully symmetric blading and in the use of the inlet enthalpy gradient as a design parameter. (Author)
NPS Report NumberNPS67-81-008
Showing items related by title, author, creator and subject.
Bell, Michael M. (Monterey, California. Naval Postgraduate School, 2010-06);Air--sea exchanges of heat and momentum are important elements in understanding and skillfully predicting tropical cyclone intensity, but the magnitude of the corresponding wind-speed dependent bulk exchange coefficients ...
Macchi, Ennio (Monterey, California. Naval Postgraduate School, 1970-08); NPS-57MA70081AThe report presents a computer program for prediction of performance of single-stage axial turbines of given geometry. The three-dimensional method developed by Vavra is applied, taking account of streamline curvatures and ...
Gany, Alon; Netzer, David W. (Monterey, California. Naval Postgraduate School, 1984-10); NPS-67-84-012The potential energetic performance of fuel ingredients for the use in the solid fuel ramjet is presented in terms of the enthalpy of combustion per unit mass and per unit volume of the fuel. Combustion phenomena and ...