Published 1983 by Naval Postgraduate School, Available from National Technical Information Service in Monterey, Calif, Springfield, Va .
Written in EnglishRead online
|Contributions||Naval Postgraduate School (U.S.). Dept. of Aeronautics|
|The Physical Object|
|Pagination||vii, 41p. :|
|Number of Pages||41|
Download A review of the design of the NPS/TPL transonic compressor
NPSCR NAVALPOSTGRADUATESCHOOL Monterey,California CONTRACTORREPORT AReviewoftheDesignoftheNPS/TPL TransonicCompressor March ContractorReport FedDocs D/2 NPSCR Approvedforpublicrelease;distributionunlimited Preparedfor: NavalPostgraduateSchool. A transonic compressor stage has been designed for the Naval Postgraduate School Turbopropulsion Laboratory.
The design relied heavily on CFD techniques while minimizing conventional empirical design methods. The low aspect ratio () rotor has been designed for a specific head ratio of and a tip relative inlet Mach number of Cited by: and analysis of a transonic axial compressor rotor with splitter blades.
Predictive numerical simulations were conducted experimental dataand were collected at the NPS TPL utilizing the Transonic Compressor Rig. This study advanced the understanding of splitter blade geometry, placement, and performancIn particular, it was e by: 1.
Naval Postgraduate School (NPS) is concentrated on the “pop-stall” problem. Investigations conducted with the Transonic Compressor Rig (TCR) are intended to improve the understanding of the nature of steam induced stall.
The present transonic compressor fan stage was designed specifically for the Naval Postgraduate School to beCited by: 1. Sanger, Nelson L., Design Methodology for the NPS Transonic Compressor, TPL Technical NoteMultidisciplinary Optimization in Turbomachinery Design, Technical Paper presented at the.
An investigation of the behavior of a transonic compressor rotor when operating close to stall is presented. The specific areas of interest are the behavior and location of low-frequency instabilities close to stall.
Design Methodology for the NPS Transonic Compressor Naval Postgraduate School, Monterey, CA. Gannon, A., Hobson, G. Using the Naval Postgraduate School's (NPS) transonic compressor design as input, the preliminary design code output was compared to the detailed throughflow design of the transonic compressor.
The. Transonic fan and compressor design. The effect of adding roughness and thickness to a transonic axial compressor rotor. Trans. R., Emmerson, P. R., Spruce, M. Analysis of aspect ratio effects on transonic rotor performance using a 3D viscous solver.
ASME paper GT, Google Scholar. A compressor has been refereed to raise static enthalpy and pressure. A successful compressor design greatly beneﬁ ts the performance of the whole power system.
Lean design methodologies have been used for industrial power system design. The compressor designs require beneﬁ t to both OEM and customers, i.e. lowest. An illustration of an open book. Books. An illustration of two cells A review of the design of the NPS/TPL transonic compressor book a film strip.
Video. An illustration of an audio speaker. Audio. An illustration of a " floppy disk. Software. An illustration of two photographs. Full text of "Transonic compressor blade tip flow visualization on a water table.". The studied rotor, NASA rotor67, is a low aspect ratio design rotor and is the ﬂrst stage rotor of a two-stage fan.
The rotor has a design pressure ratio of at a mass °ow rate of kg/sec. The design rotational speed is 16, rpm, which yields a tip speed of. Investigation of an innovative non-free vortex aerodynamic procedure to design a single-stage transonic compressor 8 June | Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, Vol.
No. Calhoun: The NPS Institutional Archive Theses and Dissertations Thesis Collection Transonic Compressor Test Rig rebuild and initial results with the Sanger stage. o design performance must be considered early in the blade design process. Recently, a new set-based design method accounting for stability at part speed as well as e ciency at the design point has been developed.
This method makes use of a global optimizer where the end result is an optimal set of compressor stages, i.e. a pareto-front, which.
American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA More information. Video Video simulation. An animation showing the entropy function at mid-span for a three-stage transonic compressor simulation. The wakes from a given blade row can still be made out even several blade rows downstream, and significant unsteadiness resulting from the mixing of the wakes is observed in the last two stages.
Performance of single-stage axial-flow transonic compressor with rotor and stator aspect ratios of andrespectively, and with design pressure ratio of The overall and blade-element performance of a low-aspect-ratio transonic compressor stage is presented over the stable operating flow range at 70, 90, and percent design speeds.
At design speed the rotor and stage achieved. In this paper, we explore the redesign of a transonic compressor using the 3D inverse design method.
In the inverse design approach, the pressure loading, blade thickness distribution and stacking axis are specified and the camber surface is calculated accordingly.
The design of modern, transonic, axial ow compressors for applications within aero engines is a very complex process that is divided into many stages. It starts with fairly primitive methods to lay out the overall design, and ends with sophisticated 3D simulations using Computational Fluid Dynamics (CFD).
In between these stages, through. Transonic axial-flow compressors are used to obtain relatively high pressure ratios within a single stage. This reduces weight and size and offers a compact design.
However, the transonic flow is sensitive to the profile shape and design of rotating and static components. Another important factor is rotor stability when approaching stall conditions. In recent years, the growth in deployment of. Compressor consumes between 55%% of the power produced by the Turbine section of the gas turbine.
Table 1 Axial Flow Compressor Characteristics Type of Application Type of Flow Inlet Relative Velocity Mach Number Pressure Ratio per Stage Efﬁ ciency per Stage Industrial Subsonic 88%% Aerospace Transonic Sanger’s NPS transonic axial compressor rotor is shown in Figure 3.
The design process and methodology followed is documented in Sanger [5, 6] which resulted in a low aspect ratio () rotor with a tip relative inlet Mach number ofand an overall stage pressure ratio of design mass ﬂow kg / s.
design sprpm outer diameter m hub-to-tip-ratio rotor blades 16 stator blades 29 Table 1: Key parameters of the Darm-stadt Transonic Compressor.
Settling chamber: 1 Intake with mass flow measurement: 2 Test compressor: 3 Torquemeter: 4 Gearbox: 5 kW DC-Drive: 6 12 3 45 6. A new, multidisciplinary algorithm for the CFD design optimization of turbomachinery blades is presented.
It departs from existing techniques in that it uses a simple, previously-developed Bezier geometry representation (BLADE-3D) that can be easily manipulated to achieve true 3. The three-stage transonic research compressor was designed to be tested in an existing single-stage test stand with a minimum of modi- fication to the test facility.
The only effect this had on the design was to fix the compressor tip diameter at 16 inches and the discharge hub-tip radius ratio at Reliability-Based Design Optimization of a Transonic Compressor Yongsheng Lian∗ University of Michigan, Ann Arbor, Michigan and Nam-Ho Kim† University of Florida, Gainesville, Florida A multiobjective, reliability-based design optimization.
An Educational Introduction to Transonic Compressor Stage Design Principles An introduction to the operational and design features of the transonic fan stage of a modern turbofan engine can give the student an example of highly developed turbomachinery whose performance and design can be readily appreciated from fundamental knowledge of.
Performance of single-stage axial-flow transonic compressor with rotor and stator aspect ratios of and respectively, and with design pressure ratio of The overall and blade-element performances of a low-aspect-ratio transonic compressor stage are presented over the stable operating flow range for speeds from 50 to percent of design.
AIChE's first manual for testing and measuring performance of centrifugal compressors. The newest addition to AIChE's long-running Equipment Testing Procedure series, Centrifugal Compressors: A Guide to Performance Evaluation and Site Testing provides chemical engineers, plant managers, and other professionals with helpful advice to assess and measure the performance of a.
cylinder design and measurement • P2 is desired delivery pressure. As long as P2 is reached, the compressor has done its job. • Only the compression process can be adjusted by varying n, the polytropic index.
• Isothermal process (n=1) results in minimum work (smallest area). • Compressors are cooled by water jackets or cooling fins. In this section of Mechanical books you will find compressor handbook pdf for direct downlod. industrial Reciprocating and Centrifugal air compressors pdf ebooks.
types of compressors, efficiency and : Report broken links to Contact us Compressors introduction Download A Practical Guide to Compressor Technology (Second Edition) Download Atlas Copco Compressed Air Manual 8th.
A Multidisciplinary Algorithm for the 3-D Design Optimization of Transonic Axial Compressor Blades [James A. Jones] on *FREE* shipping on qualifying offers.
A Multidisciplinary Algorithm for the 3-D Design Optimization of Transonic Axial Compressor BladesAuthor: James A. Jones. Preliminary Design Code for an Axial Stage Compressor [Rizwan R. Ramakdawala] on *FREE* shipping on qualifying offers.
Preliminary Design Code for an Axial Stage CompressorAuthor: Rizwan R. Ramakdawala. Bradshaw et al. () presented a comprehensive model of a miniature-scale linear compressor for electronics cooling. The model consists of a vibration sub-model that is particular to the operation of a linear compressor as well as other sub-models.
High flow coefficients on the compressor design will lead to high relative Mach numbers on the inducer (Mrel > ), to high shock losses and reduced operating range.
An important aspect to minimize the efficiency penalties expected is to leverage the learnings from axial compressor design on transonic compressor blade design. Design Approach 2 (DA2): M2 and M4: includes pulsation study with mechanical review Design Approach 3 (DA3): M2-M5: basic pulsation and mechanical analysis (resonance avoidance).
M6 and M7 studies are advanced mechanical analysis (forced response) on compressor. Current compressor development for gas turbine engines below hp indicates a promising future for axial-centrifugal compressors, particularly if the axial stage is transonic.
This forecast assumes high efficiency for the axial stage even though compressor size is 5 in. dia or less. The Boeing Co. This design eliminates a wrist-pin bearing on the piston. Piston-compressor makers also employ a variety of self-lubricating materials for the sealing rings and cylinder liners.
Rotary-screw compressor makers tighten up the clearances between the screws, eliminating the need for oil sealant. There are tradeoffs, however, with any of these schemes.
REVIEW OF PAST APPROACHES TO TIP CLEARANCE EFFECTS 4 has been commenced at the Naval Postgraduate School Turbopro-pulsion Laboratory (NPS/TPL). This report summarizes the pre-liminary work on the Multistage Compressor (MSC) facility at the Laboratory.
Main types of compressors used in industrial refrigeration are screw, piston, centrifugal and rotary vane. Another type, which is produced in large quantities, a scroll compressor, but still these compressors are not available in the amount normally encountered in industrial vane compressors are still used as a low stage compressors, but very little installed.
Control would add a compressor if the pressure fell below the lower set point and remove a compressor should the pressure go high.
If one or more VSD-controlled compressors were employed in the system, the controllers typically would set the target pressure midway between the load pressure and the unload pressure.Piping Restraint Analysis (Mechanical Review) This includes an evaluation of pipe support locations using charts, empirical calculations and good engineering design practices.
Results and Reporting Wood’s DataMiner software tool and reporting approach provide valuable information on the compressor’s pulsation predictions and performance.Annotation This book examines the full spectrum of compressor types, how they operate, how to control them, and how operating conditions can significantly impact their performance.
Discussed in detail are the influence of pressure, temperature, molecular weight, specific heat ratio, compression ratio, speed, vane position, and volume s: 1.