Author: D. C. WislerPublisher:
ISBN:
Category :
Languages : en
Pages : 86
Book Description
Preliminary Design Study of Advanced Multistage Axial Flow Core Compressors
Preliminary Compressor Design Study for an Advanced Multistage Axial Flow Compressor
Author: H. V. MarmanAerodynamic Design Study of Advanced Multistage Axial Compressor
Author: Louis M. LarosilierePublisher:
ISBN:
Category : Compressors
Languages : en
Pages : 36
Book Description
Parametric Study of Advanced Multistage Axial-flow Compressors
Author: M. L. MillerPublisher:
ISBN:
Category : Compressors
Languages : en
Pages : 76
Book Description
Aerodynamic Design of Axial-flow Compressors
Author: Lewis Research CenterPublisher:
ISBN:
Category : Axial flow compressors
Languages : en
Pages : 542
Book Description
Aerodynamic Design of Axial Flow Compressors
Author: Robert O. BullockPublisher:
ISBN:
Category : Axial flow compressors
Languages : en
Pages : 552
Book Description
Investigation of a 1500 Ft/sec, Transonic, High-through-Flow, Single- Stage Axial-Flow Compressor with Low Hub/Tip Ratio
Author: Publisher:
ISBN:
Category :
Languages : en
Pages : 375
Book Description
Complete experimental results are presented from tests of an axial compressor stage designed for a flow per frontal area of 39.7 lb/sec/ft square, a total pressure ratio of 1.912 and a tip speed of 1500 ft/sec. The performance objectives of this stage were derived from a preliminary design study of a multi-stage compressor for an advanced turbojet engine. Since the most serious aerodynamic design problems of the over-all compressor were observed to be associated with the first stage, this stage was chosen as the subject of a research program. Results of the tests indicated that, at design speed, design flow was achieved with a rotor isentropic efficiency of 90.4 percent, a stage isentropic efficiency of 88.2 percent and a stage total pressure ratio of 2.065.
Axial-flow Compressors
Author: Ronald H. AungierPublisher: American Society of Mechanical Engineers
ISBN:
Category : Science
Languages : en
Pages : 386
Book Description
This book provides a thorough description of an aerodynamic design and analysis systems for Axial-Flow Compressors. It describes the basic fluid dynamic and thermodynamic principles, empirical models and numerical methods used for the full range of procedures and analytical tools that an engineer needs for virtually any tupe of Axial-Flow Compressor, aerodynamic design or analysis activity. It reviews and evaluates several design strategies that have been recommended in the literature or which have been found to be effective. It gives a complete description of an actual working system, such that readers can implement all or part of the system. Engineers responsible for developing, maintaining of improving design and analysis systems can benefit greatly from this type of reference. The technology has become so complex and the role of computers so pervasive that about the only way this can be done today is to concentrate on a specific design and analysis system. The author provides practical methodology as well as the details needed to implement the suggested procedures.
Design of a 1500 Ft/Sec, Transonic, High-through-Flow, Single-Stage Axial-Flow Compressor with Low Hub/Tip Ratio
Author: Publisher:
ISBN:
Category :
Languages : en
Pages : 298
Book Description
This report describes the aerodynamic design of a transonic axial- flow compressor inlet stage designed for high flow rate per unit frontal area and relatively high aerodynamic loading. The performance objectives of this stage were derived from a preliminary design study of a multi-stage compressor for an advanced turbojet engine. The design goals chosen included a tip speed of 1500 ft/sec, a flow rate of 39.7 lb/sec per square foot of frontal area, a stage total pressure ratio of 1.91 and a stage isentropic efficiency of 0.83. The techniques used in the preliminary and detail designs are described. The complete aerodynamic flow field pertaining to the design point is defined on twenty-one stream surfaces, and radial and meridional distributions of significant parameters are presented. Finally, the detailed flowpath geometry is defined and airfoil coordinates are included for both stream surfaces and cartesian manufacturing sections.
Development of a Methodology to Estimate Aero-performance and Aero-operability Limits of a Multistage Axial Flow Compressor for Use in Preliminary Design
Author: Sameer KulkarniPublisher:
ISBN:
Category :
Languages : en
Pages : 112
Book Description
The preliminary design of multistage axial compressors in gas turbine engines is typically accomplished with mean-line methods. These methods, which rely on empirical correlations, estimate compressor performance well near the design point, but may become less reliable off-design. For land-based applications of gas turbine engines, off-design performance estimates are becoming increasingly important, as turbine plant operators desire peaking or load-following capabilities and hot-day operability. The current work implements a one-dimensional stage stacking procedure, including a new blockage term, which is used to estimate off-design compressor performance and operability range of a 13-stage axial compressor used for power generation. The procedure utilizes stage characteristics which are constructed from computational fluid dynamics (CFD) simulations of groups of stages. The stage stacking estimates match well with CFD results. These CFD results are used to assess a metric which estimates the stall limiting stages.