The three-dimensional laminar boundary layer on a rotating helical blade

Horlock, J. H.; Wordsworth, J.

doi:10.1017/s0022112065001374

Cited by 11 publications

(4 citation statements)

References 3 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…A calculation of the laminar velocity profiles was made using the analysis of Horlock & Wordsworth (1965). It is assumed in this analysis that there is no streamwise pressure gradient and this assumption is therefore implied in the calculation, so that for small cross-flows the Blasius solution results for the T FIGURE 7 .…”

Section: Discussionmentioning

confidence: 99%

“…On turbine blades extended areas of laminar flow are possible (see Horlock 1969). A general solution of the equations describing the laminar boundary layer on a blade rotating in a radial pressure gradient has been given (Horlock & Wordsworth 1965) and the initial object of the experiments described here was to provide measurements for comparison with this solution. Figure 1 shows the helical co-ordinate system that was used for the original t Present address : TJniversity of Salford, Salford M5 4WT, England.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Three-dimensional laminar boundary layers in crosswise pressure gradients

Horlock

Lewkowicz

Wordsworth³

1974

J. Fluid Mech.

Self Cite

View full text Add to dashboard Cite

Two attempts were made to develop a three-dimensional laminar boundary layer in the flow over a flat plate in a curved duct, establishing a negligible streamwise pressure gradient and, at the same time, an appreciable crosswise pressure gradient.A first series of measurements was undertaken keeping the free-stream velocity at about 30 ft/s; the boundary layer was expected to be laminar, but appears to have been transitional. As was to be expected, the cross-flow in the boundary layer decreased gradually as the flow became progressively more turbulent.In a second experiment, at a lower free-stream velocity of approximately 10 ft/s, the boundary layer was laminar. Its streamwise profile resembled closely the Blasius form, but the cross-flow near the edge of the boundary layer appears to have exceeded that predicted theoretically. However, there was a substantial experimental scatter in the measurements of the yaw angle, which in laminar boundary layers is difficult to obtain accurately.

show abstract

Section: Discussionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Three-dimensional laminar boundary layers in crosswise pressure gradients

Horlock

Lewkowicz

Wordsworth³

1974

J. Fluid Mech.

Self Cite

View full text Add to dashboard Cite

show abstract

“…Fogarty (1951) and Mager & Hansen (1952) were amongst the first to report that integral boundary methods demonstrated that the magnitude of the radial and streamwise components of flow in the boundary layer were comparable. Horlock & Wordsworth (1965) showed that this radial migration of flow within the boundary layer was dependent 3.…”

Section: Mid-height Boundary Layermentioning

confidence: 99%

“…This causes the bulk passage flow in the rotor to move radially outward and in the stator to move radially inward. Second, a differential boundary layer effect where the differential effect of centrifugal and Coriolis forces cause the boundary layers in the rotor to be accelerated towards the casing, Horlock & Wordsworth (1965). This effect is critical to this paper as it acts as a natural asymmetry between the way in which the rotor and stator boundary layers develop.…”

Section: Effect Of Rotationmentioning

confidence: 99%

The Effect of Reaction on Compressor Performance

Chana

Miller

2022

Journal of Turbomachinery

View full text Add to dashboard Cite

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).

show abstract

A laminar boundary layer on a rotating three-dimensional blade

Miyake

Fujita

1974

J. Fluid Mech.

View full text Add to dashboard Cite

The laminar boundary layer on a rotating thin blade of an axial turbomachine is discussed. A method of deriving the basic equations of the flow for a generalized blade configuration is described, treating a typical blade in practical use as an example. A perturbation technique is applied to obtain a series solution composed of two groups of similar functions. The results give insight into the properties of the boundary layer on helical non-loaded blades in a uniform stream, indicating the influence purely of three-dimensionality of the blade configuration.

show abstract

The three-dimensional laminar boundary layer on a rotating helical blade

Cited by 11 publications

References 3 publications

Three-dimensional laminar boundary layers in crosswise pressure gradients

Three-dimensional laminar boundary layers in crosswise pressure gradients

The Effect of Reaction on Compressor Performance

A laminar boundary layer on a rotating three-dimensional blade

Contact Info

Product

Resources

About