Last edited by Vucage
Sunday, November 1, 2020 | History

1 edition of Aerodynamic design of symmetrical blading for three-stage axial flow compressor test rig found in the catalog.

Aerodynamic design of symmetrical blading for three-stage axial flow compressor test rig

Michael Hans Vavra

Aerodynamic design of symmetrical blading for three-stage axial flow compressor test rig

Written in English

Subjects:
• Compressors,
• Aerodynamics,

The report deals with the aerodynamic design of an axial compressor stage with symmetrical bladings for a research program to investigate tip clearance effects in a three-stage compressor. It establishes the blading data and the stage performance with an iterative three-dimensional approach, and gives criteria for the drive and the flow measuring device of the test unit. The calculated distributions of the flow properties in the stage will be used for future comparisons with test data. (Author)

Edition Notes

The Physical Object ID Numbers Statement by M.H.Vavra Contributions Naval Postgraduate School (U.S.) Pagination 58 p. : Number of Pages 58 Open Library OL25494260M OCLC/WorldCa 434890881

Axial Flow Fan and Compressor Aerodynamics (35) Unsteady Flows in Turbomachinery (27) Evaluation of Compressor Blading With Blade End Slots and Full-Span Slots in a Highly Loaded Compressor Cascade Large Eddy Simulation of Combustor and Complete Single-Stage High-Pressure Turbine of the FACTOR Test Rig. Martin Thomas, Jerome Dombard.

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Aerodynamic design of symmetrical blading for three-stage axial flow compressor test rig by Michael Hans Vavra Download PDF EPUB FB2

Three blading designs of high pressure ratio axial flow fan with hub/tip ratio of were carried out with the use of compressor design technology.

The flow coefficient and/or pressure. van Rooij, MPC, Dang, TQ, & Larosiliere, LM. "Improving Aerodynamic Matching of Axial Compressor Blading Using a 3D Multistage Inverse Design Method." Proceedings of the ASME Turbo Expo Power for Land, Sea, and Air.

Volume 6: Turbo ExpoParts A and B. Reno, Nevada, USA. June 6–9, pp. by: 1. Aerodynamic Design Optimization of an Axial Flow Compressor Stator Using Parameterized Free-Form Deformation August Journal of Engineering for Gas Turbines and Power (10).

Active Stabilization of Rotating Stall in a Three-Stage Axial Compressor Joel M stability model was modified as suggested by the measurements to include the effect of blade row time lags on the compressor dynamics.

the model predicted both the mass flow at stall without control and the design parameters needed by, and the range. Axial Fans: Aerodynamic Design Th. Carolus UNIVERSITÄT SIEGEN Institut für Fluid-und Thermodynamik N/ A2 UNIVERSITÄT SIEGEN Institut für Fluid-und Thermodynamik Axial Cascade Blade Element (BE) Actual vs.

Ideal Flow Frames of References Co-ordinate System and Components of Velocity Velocity triangles on BE (turbine). The conversion of energy in an axial compressor is influenced in great measure by the surface quality of the blading.

To achieve low flow losses, the roughness values of the blade surface must be below certain limits. However, the blade surface, which is hydraulically smooth on commissioning of the machine, is in many cases attacked by dirt.

This paper presents the aerodynamic design and initial test results from a three-stage transonic compressor developed by ALSTOM Gas Turbines Ltd. The Advanced Transonic Compressor (ATC) was designed using a design system based on three-dimensional (3D) Navier-Stokes CFD codes in contrast to the more conventional design approach centred around.

A three stage axial flow compressor design and CFD analysis have been carri ed out which is m ainly aligned with small gas turbine (SGT) applications. At design speed, PR of and efficiency of.

axial-ﬂow compressor, aerodynamic design, or ana- of a three stage axial flow compressor with part load consideration in gas turbine application regarding surge margin is presented in this. Literature Review Year Author Journal/ Article Observation Mark Stevens Fan Performance Rated performance is found when flow at inlet is fully developed, symmetrical and free from swirl.

Barton Bell Test of A Single Stage Axial Flow Fan Different blade angles put different effects of flowrate, pressure and efficiency. This paper describes the introduction of three-dimension (3-D) blade designs into a 5-stage axial compressor with multi-stage computational fluid dynamic (CFD) methods.

Prior to a redesign, a validation study is conducted for the overall performance and flow details based on full-scale test data, proving that the multi-stage CFD applied is a relatively reliable tool for the analysis of the. Here, a single-stage transonic axial compressor with total pressure ratio and corrected mass flow rate of 23 kg/sec at a corrected design speed of 12, RPM is chosen.

The compressor stage aerodynamic parameters are equivalent to an axial stage of a modern aero-engine. Table 1 shows the detailed compressor stage design specifications. The 3-D turbulent flow at the exit of a single-stage axial compressor rotor passage was measured using both a hot-wire probe and a high frequency pressure probe, while the 3-D mean flow in the tip.

This paper describes a methodology Aerodynamic design of symmetrical blading for three-stage axial flow compressor test rig book a fully tested and calibrated mathematical model for the treatment of endwall effects in axial compressor aerodynamic calculations.

Additional losses and deviations caused by the clearance and secondary flows are analyzed. These effects are coupled with endwall boundary layer losses and blockage development. An axial compressor is a gas compressor that can continuously pressurize is a rotating, airfoil-based compressor in which the gas or working fluid principally flows parallel to the axis of rotation, or differs from other rotating compressors such as centrifugal compressor, axi-centrifugal compressors and mixed-flow compressors where the fluid flow will include a "radial.

Author of Aero-thermodynamics and flow in turbomachines, Compressor test rig for investigation of flow phenomena in turbo-machines, Calculating procedure of sea-level static performance of two-spool afterburning bypass jet engine, Flow in radial turbines, Design data for radial turbines, Aero-thermodynamics and flow in turbomachines, Aero-thermodynamics and flow in turbo-machines, Design.

Fig. 1 briefly depicts the test compressor with the baffle distortion generator and the flow measurement. The test rig is operated in open-loop conditions. The distortion generator is installed on the inlet section. At the outlet of the compressor, an exit throttle adjusts the back pressure of the stage.

Fig. 1 shows the detailed arrangements of measuring positions in the three-stage axial flow compressor. Previous studies, have described the measurement points of the inlet and outlet static pressures that are located six C ax upstream the first blade row and four C ax downstream the third blade row, respectively.

Three sets of high-frequency pressure transducers are mounted on the. at the root, and a fairly high ratio of axial velocity to mean blade speed.

The design was therefore of the type in which a relatively hig h work output per stage is coupled with a relatively high flow: throughout. In addition the blade profiles were laid out in a systematic manner from a standard, symmetrical aerofoil profile shape set around.

In an axial flow compressor, the axial velocity distribution in the annulus deteriorates to a parabolic form after the first two or three stages. Comparative tests described in the chapter were made on compressors designed for constant axial velocity, the actual axial velocity distribution, and increased total head rise toward the two blade.

The blades had a design flow turning angle of $$\varDelta \beta =60^\circ$$ and were arranged in an airfoil stagger angle of $$\gamma =20^\circ$$. The two test sections used for the experiments are depicted in.

The tip leakage flow is closely related to the tip clearance, which is one of the key parameters for the design and manufacture of an axial compressor. As the tip clearance is changed, not only is the strength of the leakage flow changed, but also other flow structure and distribution are influenced greatly, especially under a near-stall condition.

iii Abstract The leakage ﬂow near the tip of unshrouded rotor blades in axial turbines imposes signif-icant thermal loads on the blade. It is also responsible for up to a third of aerodynamic losses in. The aerodynamic performance of three-stage axial turbine with three different stage axial distances is experimentally measured at the air turbine test rig of Dongfang Steam Turbine Co.

LTD. Experimental results show that efficiency increases when the stage axial distance decreases for the geometry under study with relative stage distance ranged. An illustration of an open book. Books. An illustration of two cells of a film strip. Video. An illustration of an audio speaker.

Audio An illustration of a " floppy disk. Full text of "Three-dimensional Aerodynamic Instability in Multi-stage Axial Compressors" See other formats. Aerodynamic coefficients of a symmetrical airfoil in an oscillating flow (IA aerodynamiccoeff).pdf 1, × 1, pages; MB Aerodynamic design of symmetrical blading for three-stage axial flow compressor test rig (IA aerodynamicdesig00vavr).pdf 1, × 1, 66 pages; MB.

Rotating stall limits the operating range and stability of the centrifugal compressor and has a significant impact on the lifetime of the impeller blade. This paper investigates the relationship between stall pressure wave and its induced non-synchronous blade vibration, which will be meaningful for stall resonance avoidance at the early design phase.

Axial Flow Fan and Compressor Aerodynamics A New Design for Tip Injection in Transonic Axial Compressors The Design, Analysis and Test of a Unique Gas Turbine Scroll for the F, Joint Strike Fighter.

Hakan Aksoy, Stony W. Kujala, Craig W. McKeever, Automated Multiobjective Optimisation in Axial Compressor Blade Design. The Axial Flow Compressor as a High Vacuum Pump by M.

HABLANIAN NRC Equipment Corporation, Newton Highlands, Mass., U.S.A. To determine the extent of pumping action produced by an axial flow compressor at very low pressures, a small ten-stage compressor was tested in series with an oil-sealed rotary piston vacuum pump. A gas turbine power plant in Thailand had the problem of compressor blade fracture in Stages 6–8, which was caused by housing damage.

This gas turbine has a total of 15 stages. The housing damage reduced the lifetime of blades to an unacceptable level. This article shall report the solution and outcomes. Three-dimensional (3D) compressor blade models in the problematic stages were.

Haynes et al. (), using the same control scheme as Paduano et al., actively stabilized a three-stage, low-speed axial compressor and obtained an 8% increase in the operating flow range.

Gysling and Greitzer () employed a different strategy using aeromechanical feedback to suppress the onset of rotating stall in a low-speed axial compressor. The experiments reported in this paper were conducted in a two-stage axial compressor rig that consists of four blade rows forming two similar stages.

Each stage blade row had 20 rotor blades followed by 20 stator blades with C4-series airfoil. The hub and tip diameters were mm and mm, respectively, with a hub–tip ratio of 5. Design Validation through Model Fan Test. Test data for all three fans was collected from the 1/5-scale fan test rig as shown in Figure The performance test set-up was constructed using the American National Standards Institute (ANSI)/Air Movement and Control Association (AMCA) standards as a reference.

For model Reynolds number (Re) to. The compressor design configuration utilizes low aspect ratio/highly-loaded axial compressor blading combined with a centrifugal backend stage tomore» Initial testing of the compressor test rig was conducted with a vaneless centrifugal stage diffuser to allow documentation of the axial compressor.

The flows in the power turbine and nonaxisymmetric exhaust volute with struts are closely coupled and inherently unsteady for marine gas turbines, and the flow interactions between them have a significant influence on the rotor and strut blade aerodynamic force characteristics; however, the asymmetric flow interactions have not been taken into account properly in current turbine design approaches.

Aerodynamic and Performance Studies of a Three-Stage High Pressure Research Turbine With 3-D - Blades, Design Point and Off-Design Experimental Investigations Design Optimization of Axial Flow Compressor Blades With Three-Dimensional Navier-Stokes Solver.

Sang-Yun Lee, Kwang Endwall Cavity Flow Effects on Gaspath Aerodynamics in an. The Periodical Interaction of the Tip Clearance Flow in the Blade Rows of Axial Compressors.

Ronald Mailach, Helmut Sauer, Redesign of a Stage Axial-Flow Compressor Using Multistage CFD. Steven R. Wellborn, Robert A. Delaney. Aerodynamic Design of a New Five Stage Low Pressure Turbine for the Rolls Royce Trent Turbofan. This report describes (1) a wind tunnel test series conducted at moderate values of Re in which 0 less than or equal alpha.

less than or equal to /sup 0/ force and moment data were obtained for four symmetrical blade-candidate airfoil sections (NACA,H, and ), and (2) how an airfoil property synthesizer code.

Controlled-Endwall-Flow Blading for Multistage Axial Compressor Rotor. Inoue, M. Kuroumaru, M. Furukawa, Aerodynamic Modeling of Multistage Compressor Flowfields: Part 1 — Analysis of Rotor/Stator/Rotor Aerodynamic Interaction Design of New Three Stage Low Pressure Turbine for the BMW Rolls-Royce BR Turbofan Engine.

Aerofoil and Euler theories applied to Axial Pumps and Fans. Basic Aerodynamics Theory Understanding how an aeroplane derives lift with the Bernoulli's equation, and looking at the forces acting on an aeroplane in flight.

Investigation of Unsteady Flow Field in a Low-Speed One and a Half Stage Axial Compressor: Effects of Tip Gap Size on the Tip Clearance Flow Structure at Near Stall Operation.The s-era German Heinkel HeS experimental engine was the first aviation turbojet to have a compressor stage with radial flow-turning part-way between none for an axial and 90 degrees for a centrifugal.

It is known as a mixed/diagonal-flow compressor. A diagonal stage is used in the Pratt & Whitney Canada PW series of small turbofans.Abstract. This paper presents the test performance of a lightly loaded, combination radial/axial turbine for a hp, two-shaft gas turbine.

This two-stage turbine configuration which included an interstage duct and an exhaust duct discharging vertically to ambient pressure conditions, was shown to be capable of attaining an overall isentropic efficiency of percent.