Inlet Flow-Field Measurements of a Transonic Compressor Rotor Prior to and During Steam-Induced Rotating Stall PDF Download
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Author:
Publisher:
ISBN:
Category : Engines
Languages : en
Pages : 71
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Book Description
Steam leakage from an aircraft carrier catapult is sometimes ingested by the aircraft's engines upon launch which may induce compressor stall. Investigation of the phenomenon known as a "pop stall" is of particular importance as the Navy prepares to field the F35C, the aircraft carrier variant of the joint strike fighter. The single engine design of the F-35C makes this aircraft particularly susceptible to steam-induced stall during catapult launch. The present project examined compressor stall and included steady-state as well as transient measurements in the inlet of a transonic compressor prior to and during a steam-induced stall. Hotwire measurements of the inlet flow field were taken to determine an inlet turbulence intensity of 2-3% during both subsonic as well as transonic compressor operation. A 95% speed line was established from data taken from open throttle to near stall. Hot-film and Kulite pressure data taken near stall showed the existence of a stall precursor which appeared near half rotor speed. Steam was injected into the inlet; however the initial method added mass to the system and did not induce a stall. A decrease in the amplitude of the pressure trace was observed however. A stall was induced by steam ingestion ahead of the existing inlet throttle, with upstream transient measurements taken using both hot-film and Kulite pressure transducers.
Author:
Publisher:
ISBN:
Category : Engines
Languages : en
Pages : 71
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Book Description
Steam leakage from an aircraft carrier catapult is sometimes ingested by the aircraft's engines upon launch which may induce compressor stall. Investigation of the phenomenon known as a "pop stall" is of particular importance as the Navy prepares to field the F35C, the aircraft carrier variant of the joint strike fighter. The single engine design of the F-35C makes this aircraft particularly susceptible to steam-induced stall during catapult launch. The present project examined compressor stall and included steady-state as well as transient measurements in the inlet of a transonic compressor prior to and during a steam-induced stall. Hotwire measurements of the inlet flow field were taken to determine an inlet turbulence intensity of 2-3% during both subsonic as well as transonic compressor operation. A 95% speed line was established from data taken from open throttle to near stall. Hot-film and Kulite pressure data taken near stall showed the existence of a stall precursor which appeared near half rotor speed. Steam was injected into the inlet; however the initial method added mass to the system and did not induce a stall. A decrease in the amplitude of the pressure trace was observed however. A stall was induced by steam ingestion ahead of the existing inlet throttle, with upstream transient measurements taken using both hot-film and Kulite pressure transducers.
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1338
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Book Description
Author: R. J. Dunker
Publisher:
ISBN:
Category :
Languages : en
Pages : 13
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Book Description
The time-dependent three-dimensional viscous flow downstream of the rotor in a single-stage transonic axial-flow compressor without inlet guide vanes was measured and analysed at design and off-design operation conditions. Measurements were made between the blade rows and within the stator how which had been recently redesigned using a controlled diffusion blade design method. Detailed measurements of the blade surface pressure distributions were performed in order to investigate whether the favourable behaviour of controlled diffusion blades can be obtained under the real flow conditions within a turbomachine, and not only under those conditions in a cascade. These data, as well as laser-velocimetry data, indicate blade boundary layer separation under some operating conditions. The optical measurements were taken at different instantaneous rotor positions relative to the stator. These results give some insight into the unsteady flow within the stator, e.g. the development of the fluctuating velocity vectors, of the turbulence intensity, of the rotor blade wakes, and of the stator blade boundary layers. (Author).
Author:
Publisher:
ISBN:
Category : Mechanical engineering
Languages : en
Pages : 422
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Book Description
Author:
Publisher:
ISBN:
Category : Turbomachines
Languages : en
Pages : 352
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Book Description
Author:
Publisher:
ISBN:
Category : Turbomachines
Languages : en
Pages : 852
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Book Description
Author: Tony Giampaolo
Publisher: The Fairmont Press, Inc.
ISBN: 0881734136
Category : Gas-turbines
Languages : en
Pages : 426
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Book Description
The second edition of a bestseller, this comprehensive reference provides the fundamental information required to understand both the operation and proper application of all types of gas turbines. The completely updated second edition adds a new section on use of inlet cooling for power augmentation and NOx control. It explores the full spectrum of gas turbines hardware, typical application scenarios, and operating parameters, controls, inlet treatments, inspection, trouble-shooting, and more. The author discusses strategies that can help readers avoid problems before they occur and provides tips that enable diagnosis of problems in their early stages and analysis of failures to prevent their recurrence.
Author: American Society of Mechanical Engineers
Publisher:
ISBN:
Category : Engineering
Languages : en
Pages : 738
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Book Description
Author: Meherwan P. Boyce
Publisher: Elsevier
ISBN: 0080456898
Category : Mathematics
Languages : en
Pages : 956
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Book Description
The Gas Turbine Engineering Handbook has been the standard for engineers involved in the design, selection, and operation of gas turbines. This revision includes new case histories, the latest techniques, and new designs to comply with recently passed legislation. By keeping the book up to date with new, emerging topics, Boyce ensures that this book will remain the standard and most widely used book in this field. The new Third Edition of the Gas Turbine Engineering Hand Book updates the book to cover the new generation of Advanced gas Turbines. It examines the benefit and some of the major problems that have been encountered by these new turbines. The book keeps abreast of the environmental changes and the industries answer to these new regulations. A new chapter on case histories has been added to enable the engineer in the field to keep abreast of problems that are being encountered and the solutions that have resulted in solving them. - Comprehensive treatment of Gas Turbines from Design to Operation and Maintenance. In depth treatment of Compressors with emphasis on surge, rotating stall, and choke; Combustors with emphasis on Dry Low NOx Combustors; and Turbines with emphasis on Metallurgy and new cooling schemes. An excellent introductory book for the student and field engineers - A special maintenance section dealing with the advanced gas turbines, and special diagnostic charts have been provided that will enable the reader to troubleshoot problems he encounters in the field - The third edition consists of many Case Histories of Gas Turbine problems. This should enable the field engineer to avoid some of these same generic problems
Author: William J. Rae
Publisher:
ISBN:
Category :
Languages : en
Pages : 37
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Book Description
Finite-difference calculations of the flow in a transonic compressor blade row were carried out, using a radiation boundary condition at a plane upstream of the blades. These results show essentially no difference from a comparable set that were done using a uniform-flow approximation as the inlet boundary condition. (Author).
