Gas turbine engine performance requires effective and reliable internal cooling over the duty cycle of the engine. Understanding the effectiveness of cooling flows when making life predictions for rotating components subject to the main gas path temperatures is crucial. A test facility has been developed at the University of Sussex incorporating a two stage turbine designed to support a European funded research project with the objective of enhancing the understanding of interactions between main annulus gas paths and secondary air systems. This thesis describes the specific contribution of the author to the research conducted at the test facility. Non-invasive gas seeding and concentration measurement techniques together with hot geometry displacement measurements have been developed to meet three distinct objectives: to determine inter-stage seal flows between rotor disc cavities; to provide data to quantify rim seal exchange flows between rotor stator cavities and the main annulus gas path for both bulk ingestion and egress conditions; and, to provide data to quantify the re-ingestion of cooling air egressed into the main annulus gas path. Detailed knowledge of these flows is vital to understanding the flow structures within rotor stator cavities and to optimise coolant delivery methods. Experimental results are presented for a number of cooling flow supply geometries and flow rates. The gas concentration measurement techniques developed and the results obtained are compared to traditional measurements as well as numerical simulations carried out by research project partners. This work develops the measurement techniques of rotor stator cavity flows and provides data suitable for the validation of improved thermo-mechanical and CFD codes, beneficial to the engine design process.

Thèse doctorat : Génie Mécanique : Villeurbanne, INSA : 2004. / Titre provenant de l'écran-titre. Bibliogr. p. 172-175.

Thèse de doctorat : Génie mécanique : Villeurbanne, INSA : 2002. / Titre provenant de l'écran-titre. Bibliogr. p.90-95.

Thèse de doctorat : Science et ingénierie des matériaux : INPL : 2008. / Titre provenant de l'écran-titre.

No description available.

Thesis (M.S.)--Virginia Polytechnic Institute and State University, 1992. / Vita. Abstract. Includes bibliographical references (leaves 66-67). Also available via the Internet.

Thesis (Ph. D. in Aeronautics and Astronautics)--Naval Postgraduate School, June 2002. / Dissertation supervisor: Raymond P. Shreeve. Includes bibliographical references (p. 157-161). Also available online.

Thesis (M. Eng.)--Carleton University, 1992. / Also available in electronic format on the Internet.

Several theories of creep and creep rupture are reviewed. Specific attention is devoted to the brittle damage theory proposed by Kachanov. Creep, damage and life predictions for rectangular or circular cross section beams under bending and tensile loads are presented. Comparison with data for a Ni Superalloy showed life predictions could be 30X in excess of experimental values. This beam model also revealed that it is imperative that no bending moments be inadvertently applied during tensile creep testing. The creep-damage material model is extended to multidimensional situations. A refinement, whereby no damage accumulates in compression, is incorporated. A User-Material subroutine for this constitutive model has been formulated, and incorporated into the ABAQUS FEM package. Several verification examples are presented; one example is the creep-damage behaviour of a notched bar in tension. The value of reference stress techniques is discussed. Reference stress estimates for a centrifugally loaded bar, as well as for a cantilever under distributed loads, are presented. These could be useful in turbine blade design. Bibliography: pages 91-92.

The design and construction of a high-speed turbomachinery research facility is reported. This facility provides a drive system utilizing a gas turbine engine, two speed-increasing gearboxes, and interconnecting couplings to deliver 1650 HP to test rotors at speeds from 12000 to 20400 rpm in either rotational direction. A multistage axial-flow compressor was assumed as the load for initial design calculations. A vibration analysis was conducted to insure that no torsional resonances occurred within the operating range of the system. The mounting system was designed to provide a readily changeable means for interconnecting components so that numerous research activities were possible. Instrumentation, monitoring and control equipment were provided for continuous regulation of all necessary system and test parameters. / Master of Science