Blade Loading and Spanwise Effects on Wake Characteristics of Compressor Rotor Blade

1982 ◽  
Vol 19 (2) ◽  
pp. 97-103 ◽  
Author(s):  
B. Reynolds ◽  
B. Lakshminarayana
Keyword(s):  
Rotor Blade ◽  
Blade Loading ◽  
Compressor Rotor ◽  
Wake Characteristics

scholarly journals Aerodynamic Design and Testing of an Improved 1st Stage Compressor Rotor for a Heavy Duty Gas Turbine

1981 ◽  
Author(s):  
I. Ispas ◽  
H. J. Zollinger
Keyword(s):  
Gas Turbine ◽  
Rotor Blade ◽  
Aerodynamic Design ◽  
Heavy Duty ◽  
High Loss ◽  
Compressor Rotor ◽  
Performance Map ◽  
Computer Codes ◽  
Heavy Duty Gas Turbine ◽  
Design And Testing

To evaluate the potential of the compressor of Sulzer’s Typ 3 gas turbine, a series of engine tests was analyzed with two computer codes. The comparison between measured and calculated performance map are given in the paper. The design goal was to find modifications, which can be applied easily to already operating engines. The simplest option-increase of shaft speed with the existing blades-would have caused high loss due to increased tip Mach number. The calculation revealed, that a newly designed first rotor blade is an appropriate modification to increase massflow and efficiency. No further change is required, because the calculations indicate, that all subsequent stages operate at near optimum incidence. The calculations were confirmed experimentally. The paper presents the new rotor blade and its influence on the compressor calculated and measured performance.

scholarly journals Three-Dimensional Boundary Layer on a Compressor Rotor Blade at Peak Pressure Rise Coefficient

1986 ◽  
Author(s):  
B. Lakshminarayana ◽  
P. Popovski
Keyword(s):  
Boundary Layer ◽  
Rotor Blade ◽  
Peak Pressure ◽  
Pressure Coefficient ◽  
Three Dimensional ◽  
Pressure Rise ◽  
Layer Growth ◽  
Leakage Flow ◽  
Suction Surface ◽  
Compressor Rotor

A comprehensive study of the three-dimensional turbulent boundary layer on a compressor rotor blade at peak pressure rise coefficient is reported in this paper. The measurements were carried out at various chordwise and radial locations on a compressor rotor blade using a rotating miniature “V” configuration hot-wire probe. The data are compared with the measurement at the design condition. Substantial changes in the blade boundary layer characteristics are observed, especially in the outer sixteen percent of the blade span. The increased chordwise pressure gradient and the leakage flow at the peak pressure coefficient have a cumulative effect in increasing the boundary layer growth on the suction surface. The leakage flow has a beneficial effect on the pressure surface. The momentum and boundary layer thicknesses increase substantially from those at the design condition, especially near the outer radii of the suction surface.

Cold Blade Profile Generation Methodology for Compressor Rotor Blades Using FSI Approach

2017 ◽  
Author(s):  
Kirubakaran Purushothaman ◽  
Sankar Kumar Jeyaraman ◽  
Ajay Pratap ◽  
Kishore Prasad Deshkulkarni
Keyword(s):  
Aspect Ratio ◽  
Rotor Blade ◽  
Axial Compressor ◽  
Operating Conditions ◽  
Rotor Blades ◽  
Blade Profile ◽  
Interaction Technique ◽  
Compressor Rotor ◽  
Blade Shape ◽  
Blade Geometry

This paper describes a methodology for obtaining correct blade geometry of high aspect ratio axial compressor blades during running condition taking into account of blade untwist and bending. It discusses the detailed approach for generating cold blade geometry for axial compressor rotor blades from the design blade geometry using fluid structure interaction technique. Cold blade geometry represents the rotor blade shape at rest, which under running condition deflects and takes a new operating blade shape under centrifugal and aerodynamic loads. Aerodynamic performance of compressor primarily depends on this operating rotor blade shape. At design point it is expected to have the operating blade shape same as the intended design blade geometry and a slight mismatch will result in severe performance deterioration. Starting from design blade profile, an appropriate cold blade profile is generated by applying proper lean and pre-twist calculated using this methodology. Further improvements were carried out to arrive at the cold blade profile to match the stagger of design profile at design operating conditions with lower deflection and stress for first stage rotor blade. In rear stages, thermal effects will contribute more towards blade deflection values. But due to short blade span, deflection and untwist values will be of lower values. Hence difference between cold blade and design blade profile would be small. This methodology can especially be used for front stage compressor rotor blades for which aspect ratio is higher and deflections are large.

Influence of Blade Aerodynamic Loading on Efficiency of Radial-Inflow Turbines

1992 ◽  
Author(s):  
T. Takamura ◽  
F. Nishiguchi
Keyword(s):  
Shape Factor ◽  
Rotor Blade ◽  
Flow Analysis ◽  
Three Dimensional ◽  
Blade Loading ◽  
Stream Surface ◽  
Turbine Efficiency ◽  
Blade Shape ◽  
Velocity Triangle ◽  
The Mean

This paper describes the relation between turbine efficiency and rotor blade loading parameters. Tests were carried out on 12 kinds of rotors, which had the same inlet velocity triangle and meridional contour, but different blade numbers (8–11) and blade lengths. The momentum thickness and shape factor of the boundary layers obtained from the results of a quasi-three dimensional flow analysis were used as the rotor blade loading parameters. It was found that blade loading could be evaluated by the shape factor at the mean stream surface and that turbine efficiency was affected by the blade shape of the exducer.

Turbine Blade Unsteady Heat Transfer Change due to Stator Indexing

1999 ◽  
Author(s):  
David A. Johnston ◽  
Sanford Fleeter
Keyword(s):  
Heat Transfer ◽  
Heat Transfer Coefficient ◽  
Hot Spots ◽  
Rotor Blade ◽  
Unsteady Heat Transfer ◽  
Blade Loading ◽  
Second Stage ◽  
High Stage ◽  
Rotating Reference Frame ◽  
Thin Platinum

Stator indexing to alter and/or control the unsteady heat transfer of closely spaced airfoil rows in turbomachinery was studied experimentally in a two-stage low-speed research turbine. With the second vane row fixed, the inlet vane row was indexed to six positions over one vane-pitch cycle at design and high stage loadings. The aerodynamic forcing functions to the first- and second-stage rotors were measured in the rotating reference frame, with the resulting rotor blade unsteady heat transfer response quantified by an electrically heated rotor blade instrumented with thin platinum-film heat gages. The level of attenuation of unsteady heat transfer coefficient due to stator indexing was found to be both location and blade loading dependent, ranging from 10% to 80% of the maximum. Because of the attenuation’s location dependence, stator indexing is therefore best suited to minimize unsteady heat transfer in local hot spots on the blade.

Application of Detached Eddy Simulation to a Subsonic Compressor Rotor

2008 ◽  
Author(s):  
Chunwei Gu ◽  
Fan Feng ◽  
Xuesong Li ◽  
Meilan Chen
Keyword(s):  
Wake Flow ◽  
Leakage Flow ◽  
Separation Region ◽  
Detached Eddy Simulation ◽  
Tip Leakage Flow ◽  
Blade Loading ◽  
Tip Leakage ◽  
Eddy Simulation ◽  
Compressor Rotor ◽  
Des Model

An attempt is made in the present paper to apply DES (Detached Eddy Simulation), which is based on S-A model of RANS, for investigating the flow field around a subsonic compressor rotor with a tip clearance of 2% blade height. Comparison of the results by DES and S-A model shows that DES model can capture more intensive vortex flow, such as tip leakage flow, double leakage flow, as well as interaction between the leakage flow and wake flow downstream of the rotor passage. DES model predicts more complicated flow at the separation region near the hub. DES simulation for different operation conditions also reveals interesting details. The shedding angle and strength of the tip leakage flow changes with the blade loading. The starting point of the leakage vortex moves towards the leading edge when the blade loading increases. Double leakage is observed only at the design and higher loading conditions, and is not at a lower loading condition. The tip leakage vortex splits into two branches downstream of the rotor blade due to interaction with the wake flow. Instantaneous results show unsteadiness of the tip leakage vortex. Alternating regions of higher and lower loss is found along the time-averaged leakage vortex trajectory. Obvious is also the unsteadiness in the separation region near the hub.

Transonic Compressor Rotor Design Using Non-Monotonic Meanline Angle Distribution

2007 ◽  
Author(s):  
Zongjun Hu ◽  
Gecheng Zha ◽  
Matthew Montgomery ◽  
Thomas Roecken ◽  
John Orosa
Keyword(s):  
Mach Number ◽  
Rotor Blade ◽  
Angle Distribution ◽  
Stall Margin ◽  
Blade Passage ◽  
Transonic Compressor ◽  
Compressor Rotor ◽  
Rotor Design ◽  
Blade Section ◽  
Transonic Rotor

A non-monotonic meanline angle distribution technique with local negative camber is applied to a transonic rotor blade from the hub area to tip with the inlet Mach number varying from subsonic to low supersonic. The blade passage area is controlled by the non-monotonic meanline angle distribution, which results in reduced peak Mach number and weakened or removed shock wave. The negative camber is used downstream of the throat and hence it does not affect the flow passing capability of the blade section. The design point efficiency is significantly increased and the stall margin at part speed is also improved. Detailed results are given in the paper.

Design Optimization of a HP Compressor Rotor Blade and Its Hub Endwall

2008 ◽  
Author(s):  
Vicky Iliopoulou ◽  
Ingrid Lepot ◽  
Philippe Geuzaine
Keyword(s):  
Rotor Blade ◽  
Secondary Flows ◽  
Design Parameters ◽  
Present Contribution ◽  
Single Row ◽  
Compressor Rotor ◽  
Blade Shape ◽  
Shock Mechanism ◽  
Operating Points ◽  
Isentropic Efficiency

The present contribution focuses on the design of a non axisymmetric hub endwall of a HP compressor single-row rotor blade in order to improve its performance at nominal conditions. First, the validation of the optimization chain is performed with a blade shape optimization based on 48 parameters with the aim to maximize the isentropic efficiency of the HP compressor at two different operating points and with two different tip gap values. The non axisymmetric hub surface is then parameterized with 16 design parameters that can create circumferential 3D bumps and hollows of variable amplitude and length at two main control sections that follow the blade curvature. The optimized non axisymmetric hub yields a 0.4% increase of the isentropic efficiency compared to the axisymmetric case by influencing more the shock mechanism close to the wall rather than the secondary flows.

Sign in / Sign up

Export Citation Format

Share Document