Author: Roland Günter BerndtPublisher:
ISBN:
Category :
Languages : en
Pages : 392
Book Description
Actuation for Rotating Stall Control of High Speed Axial Compressors
Author: Roland Günter BerndtPublisher:
ISBN:
Category :
Languages : en
Pages : 392
Book Description
Active Control of Rotating Stall in Axial Compressors
Author: James Donald PaduanoPublisher:
ISBN:
Category : Axial flow compressors
Languages : en
Pages : 319
Book Description
Modeling and Control of Rotating Stall in High Speed Multi-stage Axial Compressors
Author: Matthew Roger FeulnerPublisher:
ISBN:
Category :
Languages : en
Pages : 272
Book Description
Compressor Surge and Rotating Stall
Author: Jan Tommy GravdahlPublisher: Springer Science & Business Media
ISBN: 1447108272
Category : Technology & Engineering
Languages : en
Pages : 233
Book Description
The series Advances in Industrial Control aims to report and encourage technology transfer in control engineering. The rapid development of control technology impacts all areas of the control discipline. New theory, new controllers, actuators, sensors, new industrial processes, computer methods, new applications, new philosophies . . . , new challenges. Much of this development work resides in industrial reports, feasibility study papers and the reports of advanced collaborative projects. The series offers an opportunity for researchers to present an extended exposition of such new work in all aspects of industrial control for wider and rapid dissemination. Operating plant as close as possible to constraint boundaries so often brings economic benefits in industrial process control. This is the conundrum at the heart of this monograph by Tommy Gravdahl and Olav Egeland on stall control for compressors. Operation of the compressor closer to the surge line can increase operational efficiency and flexibility The approach taken by the authors follows the modern control system paradigm: -physical understanding, detailed modelling and simulation studies and finally control studies. The thoroughness of the presentation, bibliography and appendices indicates that the volume has all the hallmarks of being a classic for its subject. Despite the monograph's narrow technical content, the techniques and insights presented should appeal to the wider industrial control community as well as the gas turbine/compressor specialist. M. J. Grimble and M. A.
Active Stabilization of Rotating Stall and Surge in a Transonic Single Stage Axial Compressor
Author: Harald Jürgen WeiglAnalysis of Rotating Stall Onset in High-speed Axial Flow Compressors
Author: G. J. HendricksBifurcation Based Nonlinear Feedback Control for Rotating Stall in Axial Compressors
Author: Publisher:
ISBN:
Category :
Languages : en
Pages : 18
Book Description
Classical bifurcation analysis for nonlinear dynamics is used to derive a nonlinear feedback control law that eliminates the hysteresis loop associated with rotating stall and extends the stable operating range in axial compressors. The proposed control system employs pressure rise as output measurement and throttle position as actuating signal for which both sensor and actuator exist in the current configuration of axial compressors. Thus our results provide a practical solution for rotating stall control in axial compressors.
Soil Survey in the Netherlands
Author: A Control Volume Model of Rotating Stall in Multistage Axial Compressors
Author: Steven Gordon KoffDelay of Rotating Stall in Compressors Using Plasma Actuation
Author: Farzad AshrafiPublisher:
ISBN: 9781321613261
Category :
Languages : en
Pages : 106
Book Description
Rotating stall is a well-known aerodynamic instability in compressors that limits the operating envelope of aircraft gas turbine engines. An innovative method for suppressing the most common form of rotating stall inception using an annular DBD plasma actuator had been proposed. A DBD plasma actuator is a simple solid-state device that converts electricity directly into flow acceleration through partial air ionization. However, the proposed concept had only been preliminarily evaluated with simple numerical simulations on an isolated axial rotor using a relatively basic CFD code. The current project provides both an experimental and a numerical assessment of this concept for an axial compressor stage as well as centrifugal compressor stage that are both part of a low-speed two-stage axial-centrifugal compressor test rig. The two configuration studied are the two-stage configuration with a 100 mN/m annular casing plasma actuator placed just upstream of the axial rotor leading edge, and the single-stage centrifugal compressor with the same actuator placed upstream of the impeller leading edge. The tested configuration were simulated with a sophisticated commercial RANS CFD code (ANSYS CFX) in which was implemented the latest engineering DBD plasma model and dynamic throttle boundary condition, using single-passage multiple blade row computational domains. The experiments show that the casing plasma actuator reduces the mass flow of the last stable point (stall point) by 19.28% for the axial compressor stage and 28.39% for the centrifugal compressor stage for which the impeller is the source of rotating stall. The CFD simulations indicate that in both types of compressors the actuator delays the stall inception by pushing the incoming/tip clearance flow interface downstream into the blade passage. In each case, the predicted percentage reduction in stalling mass flow matches the experimental value reasonably well. However, the CFD simulations over-predicts the mass flow of the stall point as well as the pressure rise of the centrifugal stage and under-predict the pressure rise of the axial stage. The main factors for the difference are likely slight discrepancies between the simulated and actual axial rotor blade geometry deformation and the inability of the simulation tool to accurately capture the total pressure loss in the hub region of the vaneless diffuser.