Author: Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 534
Book Description
Secondary Flows and Endwall Boundary Layers in Axial Turbomachines
Author: Secondary Flows and Endwall Boundary Layers in Axial Turbomachines
Author: Secondary Flows and Endwall Boundary Layers in Axial Turbomachines
Author: Secondary Flows and Endwall Boundary Layers in Axial Turbomachines
Author: C. H. SieverdingAnnulus Wall Boundary Layers in Turbomachines
Author: J. H. HorlockPublisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 80
Book Description
The paper reviews a substantial body of fundamental and applied research work on the subject of annulus wall boundary layers in turbomachines. A product of this work is a method for predicting, with reasonable accuracy, the full three-dimensional boundary layer that develops through a single blade row. The limitations of the method are discussed in relation to the experimental information available to the authors. In Part 2 the fundamental work is subjected to scrutiny in order to extract a boundary layer calculation method suitable for estimating the effects of annulus wall boundary layers on the performance of turbomachines. It is shown that a great many assumptions and simplifications are necessary at the present time but that reasonably satisfactory estimates are nevertheless possible. A computer program for the estimation of annulus blockage is listed.
Control of Secondary Flow in the Wall Boundary Layers of Axial Turbomachines
Author: Massachusetts Institute of Technology. Gas Turbine LaboratoryPublisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 27
Book Description
Thermodynamics and Fluid Mechanics of Turbomachinery
Author: A. Ş ÜçerEndwall boundary layer flows and losses in axial turbomachines
Author: Ian Henry HunterComparison of Secondary Flows and Boundary-layer Accumulations in Several Turbine Nozzles
Author: Milton G. KofskeyPublisher:
ISBN:
Category : Air flow
Languages : en
Pages : 68
Book Description
An investigation of secondary-flow loss cores originating in turbine nozzle blade passages was conducted by means of flow visualization studies and detailed flow measurements. The degree of which blade surface velocity profiles affect the magnitude and concentration of loss cores was investigated by comparing three nozzle blade configurations.
Detailed Flow Measurements in Casing Boundary Layer of 429-meter-per-second-tip-speed Two-stage Fan
Author: William T. GorrellPublisher:
ISBN:
Category : Impellers
Languages : en
Pages : 40
Book Description
Detailed flow measurements made in the casing boundary layer of a two-stage transonic fan are summarized. These measurements were taken at stations upstream of the fan, between all blade rows, and downstream of the last blade row. At the design tip speed (429 m/sec) the fan achieved a peak efficiency of 0.846 at a pressure ratio of 2.471. The boundary layer data were obtained at three weight flows at the design speed: one near choke flow, one near peak efficiency, and one near stall. The data presented show steep axial velocity profiles at the stator exits were not as steep as those at the rotor exits. The data also show overturning of the flow at the tip at the stator exits. The effect of mixing is shown by the redistribution of the first-stage rotor-exit total temperature profile as is passes through the following stator.