3 edition of Blockage development in a transonic, axial compressor rotor found in the catalog.
Blockage development in a transonic, axial compressor rotor
by National Aeronautics and Space Administration, National Technical Information Service, distributor in [Washington, D.C, Springfield, Va
Written in English
|Statement||Kenneth L. Suder.|
|Series||NASA technical memorandum -- 113115.|
|Contributions||United States. National Aeronautics and Space Administration.|
|The Physical Object|
of a transonic axial compressor using NASA Rotor Kim et al. [5, 6] reported on parametric study and optimization of a circumferential casing groove combined with tip injection three design using parameters, i.e., the leading edge length, the trailing edge length, and the height of the casing groove in a transonic axial compressor. Sanders A J, Paplia J and Fleeter S A PIV investigation of rotor - IGV interactions in a transonic axial-flow compressor 35th AIAA/ASME/SAE/ASEE Joint Propulsion Conf. (Los Angeles, CA, June , ) AIAA
axial compressor rotor was studied by Suder6, and the impact of shocks on blockage was investigated. Chima 7 studied the tip clearance effects on a transonic compressor rotor. Shape optimization of a transonic axial compressor rotor operating at the design flow condition has been performed using the response surface method and three-dimensional Navier-Stokes analysis.
View Notes - NASA-Suder_blockage from BTEH at Ms Ramaiah Institute Of Technology. NASA Technical Memorandum Blockage Development in a Transonic, Axial Compressor Rotor . The near casing flow fields inside the rotor passage of a stage axial compressor with different blade-loading levels and tip gap sizes were measured by using stereoscopic particle image velocimetry (SPIV). Based on a carefully defined blockage extracting method, the variations of blockage parameter inside the blade passage were analyzed. It was found that the variation of blockage.
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A detailed experimental investigation to understand and quantify the development of loss and blockage in the flow field of a transonic, axial flow compressor rotor has been undertaken.
Detailed laser anemometer measurements were acquired upstream, within, and downstream of a transonic, axial compressor rotor operating at design and off-design. Detailed laser anemometer measurements were acquired upstream, within, and downstream of a transonic, axial compressor rotor operating at85, 80, and 60 percent of design speed, which provided inlet relative Mach numbers at the blade tip of,andby: the development of blockage in the ﬂow ﬁeld of a transonic, axial ﬂow compressor rotor (NASA Rotor 37) has been undertaken.
Detailed laser anemometer measurements were acquired upstream, within, and downstream of a transonic, axial compressor rotor operating at %, 85%, 80%, and 60% of design speed which provided inlet. In Press, Corrected Proof What are Corrected Proof articles?. Parametric investigation on a transonic axial compressor stage using CFD techniquesAuthor: M.
Ayesha Khan, P. Arunagiri, G. Antony Samuel Prabu. The estimates provided by this simplified method capture the trends in blockage with changes in design parameters to within 10 percent. More importantly, however, the method provides physical insight into, and thus guidance for control of, the flow features and phenomena responsible for compressor endwall blockage by: Design and Development of Transonic Axial Flow Compressor Rotor Blade 1.
International Journal of Engineering Research and Development e-ISSN: X, p-ISSN: X, Vol Issue 4 (April ), PP 22 Design and Development of Transonic Axial Flow Compressor Rotor Blade K Balaji1, S Emilon Zeon Rajan2, C Ganesan3, M.
The transonic axial compressor NASA Rotor 67 was adopted in this investigation. The detail geometry and performance parameters of NASA Rotor 67 can be found in Ref.
Some main design parameters are listed in Table 1. The rotating stall of NASA Rotor 67 occurs in the blade tip region, which is related to the tip leakage vortex.
An improved blockage indicator has been proposed to estimate the blockage in the transonic rotor. The results show that the tip clearance has a significant influence on the blockage in the rotor.
The tip clearance flow and the main flow is interacted with each other, and the interface between them is becoming parallel to the blade leading edge. Effects of axial and tangential blade curvature were separately analyzed.
A commercial CFD package which solves the Reynolds-average Navier-Stokes equations was used to compute the complex flow field of transonic compressor rotors. The code was validated against NASA Rotor 37. A multi-objective optimization of a coupled casing treatment (CCT) for an axial transonic compressor is performed in this study.
The coupled casing treatment is the basis axial sl. A detailed experimental investigation to understand and quantify the development of blockage in the flow field of a transonic, axial flow compressor rotor (NASA Rotor. A detailed experimental investigation to understand and quantify the development of blockage in the flow field of a transonic, axial flow compressor rotor (NASA Rotor 37) has been undertaken.
In particular, the development of blockage due to large tip-leakage flows can be a key component leading to an understanding of stage matching for multistage machines. To assess blockage related to increased tip clearance, a series of measurements are presented here from a three-stage axial compressor at two loading conditions on the %.
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.
Get this from a library. Blockage development in a transonic, axial compressor rotor. [Kenneth L Suder; United States. National Aeronautics and Space Administration.]. CiteSeerX - Document Details (Isaac Councill, Lee Giles, Pradeep Teregowda): A detailed experimental investigation to understand and quantify the development of blockage in the flow field of a transonic, axial flow compressor rotor (NASA Rotor 37) has been undertaken.
Detailed laser anemometer measurements were acquired upstream, within, and downstream of a transonic, axial compressor rotor. User Tools. Cart. Sign In. The design of radial compressor inlets for transonic flow is examined. A theoretical model  quantifies the losses in the tip sections caused by the choke margin (incidence) and the blockage of.
20% rotor axial chord coverage. 40% rotor axial chord coverage. 60% rotor axial chord coverage. 80% rotor axial chord coverage. % rotor axial chord coverage.
Greek letters θ. temperature ratio, θ ≈ T a t m T s e a l e v e l, T sealevel ≈ K. pressure ratio, δ≈ P a t m P s e a l e v e l, P sealevel ≈1. In transonic axial compressor, rotor tip leakage vortex interaction with shock layer and shroud boundary layer leads to total pressure loss and initiation of stall phenomenon.
Effect of tip winglets are investigated in compressor rotor cascade. Specifically, the relevant validation is conducted through a typical transonic axial-flow compressor, which shows that the predicted stall inception point agrees well with the experimental result.
Furthermore, the compressor is also adopted as a prototype, from which a series of forward- and backward-swept rotors are modeled. Experimental and Computational Investigation of the Tip Clearance Flow in a Transonic Axial Compressor Rotor Experimental and computational techniques are used to investigate tip clearance flows in a transonic axial compressor rotor at design and part speed conditions.
Laser anemometer data acquired in the endwall region are presented for operating conditions near peak. Jang C. M., Samad A.
and Kim K. Y. Optimal Design of Swept, Leaned and Skewed Blades in a Transonic Axial Compressor Proceedings of GT, ASME Turbo ExpoGT Crossref Google Scholar.