涡桨发动机风车特性评估方法及试飞验证  

Evaluation Method of Turboprop Engine Windmill Characteristics and Flight Test Verification

作　　者：赵海刚[1] 王朝蓬[1] 任丁丁 ZHAO Hai-gang;WANG Zhao-peng;REN Ding-ding(Chinese Flight Test Establishment,Aviation Industry Corporation of China,Xi'an 710089,China)

机构地区：[1]中国航空工业集团公司,中国飞行试验研究院,西安710089

出　　处：《科学技术与工程》2021年第4期1649-1653,共5页Science Technology and Engineering

摘　　要：涡桨发动机在空中起动之前的风车状态会产生一定的风车阻力,严重影响飞机的操纵性和稳定性,因此需进行风车阻力特性的准确计算评估,以化解飞行风险。针对涡桨发动机装机飞行中的风车特性,采用基于标准桨特性图修正原理,建立计算评估方案,并以某型涡桨发动机设计定型试飞为依托,进行不同工况下的试飞验证研究。结果表明:在相同高度,低速风车状态下,风车阻力随着速度增加而增大,而高速风车状态下,风车阻力随着速度增加而减小;随着高度增加,低、高速风车阻力均减小;低速风车状态下,桨叶角基本处于限动位,而转速随着速度增加而增加;高速风车状态下,转速达到平衡转速,桨叶角随着速度的增加而增大。可见,建立的涡桨发动机风车阻力计算方法合理、可行,计算结果精度满足试飞要求,能够为后续涡桨发动机空中起动科目的飞行试验提供技术支撑。The windmill state of turboprop engine before air-start could produce a certain amount of windmilling drag,which may affect the operability and stability of the aircraft seriously.It is necessary to calculate the windmilling drag characteristics accurately to avoid risk.Aiming at the characteristics of windmill in the flight of a submerged engine,a calculation-evaluation scheme was established based on the correction principle of the characteristic diagram of standard propeller.A certain type of turboprop engine was flight-tested under different conditions.Results show that at the same height,in the case of low speed windmill,the windmilling drag increased with the increase of speed,while it decreased with the increase of speed in the case of high-speed windmill.With the increase of height,the windmilling drag of both low and high speed decreased.In the case of low speed windmill,the blade angle was in the limit position,while the rotation speed increased with the speed.In the case of high-speed windmill,the rotation speed reached the equilibrium speed,the blade angle increased with the speed.It was shown that the proposed method of windmilling drag calculation for turboprop engine was reasonable and feasible,and the accuracy satisfied the requirements of flight test,which provided a technical support for the flight test of turboprop engine in the air-start subject in the future.

关 键 词：特性图 风车状态 功率系数 拉力系数 风车阻力 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]