Kavanagh, Patrick, "Through-flow solution for axial turbomachine blade rows " (1964). Retrospective Theses and Dissertations. Paper 3857. 1964 Signature was redacted for privacy.

Industrial turbomachinery design requires fast and reliable algorithms for the numerical optimization of design parameters that innuence the ow in the turbomachine. The problem considered in this paper is to determine the cross-sectional shape of a blade in a turbomachine in order to reproduce as well as possible a given velocity proole of the ow around the blade. It is formulated as a least sq...

Two global optimization algorithms, namely Genetic Algorithm (GA) and Simulated Annealing (SA), have been applied to the aerodynamic shape optimization of transonic cascades; the objective being the redesign of an existing turbomachine airfoil to improve its performance by minimizing the total pressure loss while satisfying a number of constraints. This is accomplished by modifying the blade ca...

The mixing-plane method for calculating the three-dimensional flow through multistage turbomachinery is used to perform flutter analysis on a single stage transonic compressor. The turbomachine considered is composed of an inlet guide vane (IGV) and a compressor blade (NASA Rotor 67). The mixing-plane boundary condition enables steady and unsteady computation of the flow through multiple blade ...

A Blade Tip Timing (BTT) system enables the measurement of turbomachinery blade vibrations by means of contactless sensors mounted in the casing. In addition, the so-called Blade Tip Clearance (BTC) measurement system ensures the monitoring of the existing running gaps between the blade tip and the casing. This paper focuses on the results achieved so far using a novel magnetoresistive sensor f...

An approximate numerical mthod is presented for analysis and determination of modal characteristics in straight, pretwisted non-unifom helicopter blades. The analysis considers the coupled flapwise bending (out of plane), chordwise bending (in plane), and torsion vibration of both rotating and non-rotating blades. The proposed method is based on the integral expansion of Green functions (struct...

An approximate numerical mthod is presented for analysis and determination of modal characteristics in straight, pretwisted non-unifom helicopter blades. The analysis considers the coupled flapwise bending (out of plane), chordwise bending (in plane), and torsion vibration of both rotating and non-rotating blades. The proposed method is based on the integral expansion of Green functions (struct...