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The effect of tip clearance on an axial flow fan
(Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1955], 1955)
The effect of tip clearance on the performance of a single stage axial flow (6000 cfm) fan was investigated for tip clearances ranging from 0.003 in. to 0.252 in. It was found that, at the rated flow, the stagnation pressure ...
Measurements of rotor stalling in a matched and a mismatched multistage compressor
(Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1995], 1995)
This paper presents the results from a set of experiments on stall inception in multistage axial flow compressors. The experiments were tailored to investigate phenomena having a wide range of time and length scales. This ...
Computational simulation of unsteady flow in transonic compressor rotor
(Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1986], 1986)
The unsteady flow about a section of a modern first stage transonic compressor rotor was simulated using a finite difference approximation to the two-dimensional, Reynolds averaged, unsteady, compressible, viscous Navier-Stokes ...
Rotor wake behavior in a transonic compressor stage and its effect on the loading and performance of the stator
(Cambridge, Mass. : Gas Turbine & Plasma Dynamics Laboratory, Massachusetts Institute of Technology, [1980], 1980)
The structure and behavior of wakes from a transonic compressor rotor and their effects on the loading and performance of the downstream stator have been studied experimentally. The rotor is 2 feet in diameter with a tip ...
Asymmetric inlet flow in axial turbomachines
(Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, 1959, 1959)
A modified actuator disc analysis is made which, through an improved prediction of the blade forces, attempts to give closer correspondence with experiment than the previous theory. The fluid is assumed inviscid and ...