Tip clearance

About: Tip clearance is a research topic. Over the lifetime, 2637 publications have been published within this topic receiving 32671 citations.

Tip clearance measurement

Abstract: An aircraft is provided and includes an airframe, first and second main rotors rotatably supported on the airframe to rotate about a rotational axis in opposite directions, first and second emitters disposed on an emitter blade of the second main rotor, each of the first and second emitters being configured to emit an emission toward a detector blade of the first main rotor, a detector disposed on the detector blade of the first main rotor, the detector being configured to detect the emissions of the first and second emitters and a flight computer which determines a clearance between the first and second main rotors in accordance with detections of the emissions by the detector.

The Characteristics of Tip Leakage in Scroll Compressors for Air Conditioners

Abstract: This Paper describes the characteristics of tangential and radial leakage which is occurring at micro tip clearance in a scroll compressor for an air conditioner (R22) under actual operating condition. It is well known that leakage phenomena have a large effect on the performance of a scroll compressor. But the leakage phenomena of a scroll compressor under actual operating condition were not clear because of a complex sealing mechanism and two phase flow. To define complex tip leakage phenomena under actual operating condition, experimental research was executed by using indirect flow rate measuring method. And analysis model of tip leakage was made for analyzing tangential and radial leakage occurring at grooves and contact points of a tip seal. In case of no oil, it was also validated as theoretical result was compared with experimental result. Therefore the quantity of tip leakage with pressure ratio, orbiting angle, discharge pressure, tip clearance, and leakage point was found out. Also it was known that tip leakage at tip part occurs somewhat although a tip seal has sealing effect for radial leakage.

Aircraft gas turbine engine backbone deflection control

Abstract: A gas turbine engine backbone deflection control apparatus to counter the effects of backbone bending due to gust, thrust. and maneuver loads by introducing a controlled backbone counter-bending moment by applying controlled tensioning forces only between axially spaced apart frames connected by the backbone. One embodiment of the invention, for a high bypass ratio turbofan engine, provides a hydraulically powered actuator to produce tensioning forces in cables connected between a fan frame and a turbine frame and the actuator is controlled by the engines digital electronic control system using input signals generated by inlet moment load sensors and/or blade tip clearance sensors.