A laminar boundary layer on a rotating three-dimensional blade

Miyake, Yutaka; Fujita, Satoko

doi:10.1017/s0022112074001492

Cited by 4 publications

(1 citation statement)

References 4 publications

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“…rotor stator upon the blade stagger angle and rotational speed. Later studies by Banks & Gadd (1963), Morris (1981) and Miyake & Fujita (1974) observed similar results to Horlock & Wordsworth. All of these early studies rely on simple analytical models of radial boundary layers, which were validated in simple, idealised, rotating disc experiments.…”

supporting

confidence: 71%

The Effect of Reaction on Compressor Performance

Chana

Miller

2022

Journal of Turbomachinery

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Reaction is the fundamental parameter by which the asymmetry of the velocity triangle of a stage is set. Little is understood about the effect that reaction has on either the efficiency or the operating range of a compressor. A particular difficulty in understanding the effect of reaction is that the rotor and stator have a natural asymmetry caused by the centrifugal effects in the rotor boundary layer being much larger than that in the stator boundary layer. In this paper a novel approach has been taken: McKenzie's ‘linear repeating stage’ concept is used to remove the centrifugal effects. The centrifugal effects are then reintroduced as a body force. This allows the velocity triangle effect and centrifugal force effect to be decoupled. The paper shows the surprising result that, depending on how the solidity is set, a 50% reaction stage can either result in the maximum, or the minimum, profile loss. When the centrifugal effects are removed, 50% reaction is shown to minimise endwall loss, maximise stage efficiency and maximise operating range. When the centrifugal effects are reintroduced, the compressor with the maximum design efficiency is found to rise in reaction by 5% (from 50% reaction to 55% reaction) and the compressor with the maximum operating range is found to rise in reaction by 15% (from 50% reaction to 65% reaction).

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supporting

confidence: 71%

The Effect of Reaction on Compressor Performance

Chana

Miller

2022

Journal of Turbomachinery

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The three-dimensional boundary layer on a rotating helical blade

Morris

1981

J. Fluid Mech.

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The development of a laminar boundary layer on a twisted helical blade is described. An appropriate co-ordinate system is developed in which the boundary-layer equations have a relatively simple form. The choice of blade geometry and the free-stream conditions result in a constant-pressure flow. This permits the flow to be considered the analogue, in a rotating frame, of the zero-pressure-gradient flat-plate boundary layer in a stationary frame. The boundary-layer equations are solved using a double series expansion in powers of distance from the leading edge and the cosine of the blade twist angle. Chordwise and spanwise velocity profiles are calculated. The variation in the skin friction coefficients is calculated as a function of position on the blade.

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