Axial compressor

About: Axial compressor is a research topic. Over the lifetime, 12035 publications have been published within this topic receiving 127766 citations.

Hybrid propulsive engine including at least one independently rotatable compressor rotor

Abstract: One aspect relates to a hybrid propulsive technique, comprising providing at least some first thrust associated with a flow of a working fluid through at least a portion of an at least one axial flow jet engine. The hybrid propulsive technique includes extracting energy at least partially in the form of electrical power from the working fluid, and converting at least a portion of the electrical power to torque. The hybrid propulsive technique fiuther includes rotating an at least one substantially axial-flow independently rotatable compressor rotor at least partially responsive to the converting the at least a portion of the electrical power to torque.

Integrated control of rotating stall and surge in aeroengines

Abstract: Aeroengines operate in regimes for which both rotating stall and surge impose low flow operability limits. Thus, active control strategies designed to enhance operability of aeroengines must address both rotating stall and surge as well as their interaction. In this paper, a nonlinear control strategy is designed based on an analytical model to achieve simultaneous active control of rotating stall and surge in an axial flow compression system with relevant dynamics representative of modern aeroengines. The controller is experimentally validated on a 3-stage low-speed axial flow compression system. This rig is dynamically scaled to replicate the interaction between rotating stall and surge typical of modern aeroengines, and several experimental results are presented for this rig. For actuation, the control stategy utilizes a single plenum bleed valve with bandwidth on the order of the rotor frequency. For sensing, measurements of the circumferential asymmetry and annulus-averaged unsteadiness of the flow through the compressor are used. Experimental validation of simultaneous control of rotating stall and surge with minimal sensing and actuation requirements is viewed as an important step towards applying active control to enhance operability of compression systems in modern aeroengines.

The Use of Sweep and Dihedral in Multistage Axial Flow Compressor Blading: Part II — Low and High Speed Designs and Test Verification

Abstract: This paper describes the introduction of 3D blade designs into the core compressors of the Rolls-Royce Trent engine series with particular emphasis on the use of sweep and dihedral in the rotor designs. It follows the development of the basic ideas in a university research project, through multistage low-speed model testing, to their application to the high pressure engine compressor. An essential element of the project was the use of multistage CFD and some of the development of the method to allow the designs to take place is also discussed. Part I of the paper concentrated on the fundamental university-based research and the methods development. Part II describes additional low-speed multistage design and testing and the high-speed engine compressor designs and tests.Copyright © 2002 by ASME

Deflector for controlling entry of cooling air leakage into the gaspath of a gas turbine engine

Abstract: The invention provides a deflector for redirecting cooling air leakage to improve the efficiency of a gas turbine engine. A conventional gas turbine engine includes a forward stator assembly and a rotor assembly with an air cooled rotor disc, and a circumferential array of blade retention slots. An array of air cooled rotor blades with blade bases are retained in each slot. The rotor blades are disposed equidistantly about the circumference of the rotor disc with a radially extending gap between each adjacent rotor blade. It is the significant detrimental effect of cooling air leakage into these gaps, which is the focus of this invention. The invention relates to providing a deflector, disposed circumferentially on a forward face of the coverplate, for deflecting cooling air leakage, flowing from the running seal through the cooling air leakage path, away from the gaps between the blades, onto the outward surface of the blade platform, and into the gaspath at an acute angle relative to rearwardly axial flow therein.

Gas turbine power plant

Abstract: A TURBO-FAN POWER PLANT IS DISCLOSED IN WHICH THEY ARE TWO INDEPENDENT FANS IN THE FAN DUCT RESPECTIVELY DRIVEN BY A GAS GENERATOR AND AN INDEPENDENT FREE TURBINE. THE GAS GENERATOR INCLUDES IN AXIAL FLOW SERIES LOW, INTERMEDATE AND HIGH PRESSURE COMPRESSOR RESPECTIVELY DRIVINGLY INTERCONNECTED WITH HIGH, INTERMEDIATE AND LOW PRESSURE TURBINES, THE INTERMEDIATE PRESSURE TURBINE BEING DRIVING- LY CONNECTED TO THE UPSTREAM OR FRONT OF THE TWO FAN THE DRIVE ARRANGEMENT OF THE FANS AND THEIR AXIAL SPACING ENABLES THEM TO ROTATE AT RELATIVELY LOW SPEEDS AND SUB STANTALLY WITHOUT ANY WAKE INTERACTION THEREBETWEEN , WHEREBY THE OVERALL NOISE OF THE POWER PLANT IS REDUCED.