This thesis presents a detailed experimental investigation of the effects of inlet skew on the secondary flows and losses in a linear cascade of high turning turbine rotor blades. The blade that was used was modified from its original design to give aerodynamic similarity in the cascade flow conditions. Three levels of inlet skew were investigated using pressure probe instrumentation and the surface oil flow technique of flow visualisation. The results have shown that inlet skew has a profound effect on the secondary flows and on the magnitude of the secondary losses. The flowfield of the cascade was modelled using several computer models. Although reasonable results were obtained with a fully viscous three-dimensional code the other models were unable to predict accurately the magnitude of the losses or even the relative effect of inlet skew on the losses. This thesis also presents measurements of the turbulent flowfield of a similar linear cascade. It was found that regions of high turbulent kinetic energy were associated with regions of high total pressure loss. It was also found that the mass averaged total pressure loss and turbulent kinetic energy followed similar distributions in the cascade.

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Bibliography: leaves 164-172. / xii, 172 leaves : ill. (some col.) ; 30 cm. / Title page, contents and abstract only. The complete thesis in print form is available from the University Library. / The task of calculating the aerodynamic load distribution on a thin three-dimensional lifting surface or wing of finite aspect ratio at small angle of attack presents difficulties for most numerical methods. The two-dimensional lifting-surface integral equation that must be solved is highly singular, and does not possess analytic solutions, even for simple plan-form geometries such as rectangles or ellipses. / Thesis (Ph.D.)--University of Adelaide, Dept. of Applied Mathematics, 1998

Bibliography: leaves 164-172. / xii, 172 leaves : ill. (some col.) ; 30 cm. / Title page, contents and abstract only. The complete thesis in print form is available from the University Library. / The task of calculating the aerodynamic load distribution on a thin three-dimensional lifting surface or wing of finite aspect ratio at small angle of attack presents difficulties for most numerical methods. The two-dimensional lifting-surface integral equation that must be solved is highly singular, and does not possess analytic solutions, even for simple plan-form geometries such as rectangles or ellipses. / Thesis (Ph.D.)--University of Adelaide, Dept. of Applied Mathematics, 1998

Thesis (Ph. D.)--University of Adelaide, Dept. of Mechanical Engineering, 1984. / A supplement to this thesis containing tabulations of all acoustic data is available from the Department of Mechanical Engineering, University of Adelaide. Includes bibliographical references (leaves 109-113).

Thesis (Ph. D.)--University of Adelaide, Dept. of Applied Mathematics, 1998. / Includes bibliographical references (leaves 164-172).

Thesis (Ph.D)--Aerospace Engineering, Georgia Institute of Technology, 2008. / Committee Chair: Ahuja, Krishan K.; Committee Member: Cunefare, Kenneth; Committee Member: Lieuwen, Tim C.; Committee Member: Mendoza, Jeff; Committee Member: Sankar, Lakshmi.

Thesis (Ph. D.)--University of Hong Kong, 1998. / Includes bibliographical references (leaf 246-270).

Thesis (M. A.)--Florida State University, 2005. / Advisor: Krothapalli Anjaneyulu, Florida State University, College of Engineering, Dept. of Mechanical Engineering. Title and description from dissertation home page (viewed Jan 27, 2006). Document formatted into pages; contains x, 72 pages. Includes bibliographical references.

Dissertation (Ph.D.)--University of Toledo, 2010. / Typescript. "Submitted to the Graduate Faculty as partial fulfillment of the requirements for the Doctor of Philosophy Degree in Engineering." "A dissertation entitled"--at head of title. Title from title page of PDF document. Bibliography: p. 152-156.