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AVIC COMMERCIAL AIRCRAFT ENGINE CO LTD

Overview
  • Total Patents
    157
  • GoodIP Patent Rank
    16,762
  • Filing trend
    ⇩ 100.0%
About

AVIC COMMERCIAL AIRCRAFT ENGINE CO LTD has a total of 157 patent applications. It decreased the IP activity by 100.0%. Its first patent ever was published in 2011. It filed its patents most often in China. Its main competitors in its focus markets engines, pumps and turbines, computer technology and environmental technology are AVIC SHENYANG ENGINE DESIGN & RES INST, AECC HUNAN POWER MACHINERY RES INSTITUTE and PAYNE MICHAEL.

Patent filings in countries

World map showing AVIC COMMERCIAL AIRCRAFT ENGINE CO LTDs patent filings in countries
# Country Total Patents
#1 China 157

Patent filings per year

Chart showing AVIC COMMERCIAL AIRCRAFT ENGINE CO LTDs patent filings per year from 1900 to 2020

Top inventors

# Name Total Patents
#1 Yin Kai 9
#2 Hou Naixian 9
#3 Chen Jun 8
#4 Guo Desan 7
#5 Chen Xiao 7
#6 Zhang Rong 7
#7 Gu Wei 6
#8 Zeng Qinglin 6
#9 Li Bin 6
#10 Wei Fang 5

Latest patents

Publication Filing date Title
CN106762813A A kind of fan blade
CN107013941A Combustion chamber fuel nozzle arrangement
CN106988787A Rotor blade and turbomachine
CN106945302A Fiber-reinforced composite fan blade and its manufacture method
CN106934074A Global optimum's fanjet air intake duct noise abatement method for designing
CN106919724A Fanjet by-pass air duct noise abatement method for designing
CN106917931A The remove device of Aero-engine Bearing chamber ventilation duct wall lubricating oil
CN106908245A Aero Engine Testing device stable state TT&C system and its data sharing method
CN106907242A Aero-engine impeller
CN106884873A Rolling bearing and aero-engine
CN106882390A Airplane air entraining precooling heat regenerative system
CN106874526A The generation method and device of the production coordinate of turbine blade
CN106834992A TiAl alloy casting and its handling process
CN106812723A blade, turbine and compressor
CN106812555A Turbo blade
CN106677834A Bolt connecting structure and method connecting low-pressure turbine disc and rotor supporting conical arm
CN106555618A The tip clearance control system of gas turbine and its method
CN106557418A For the method and apparatus of software test
CN106555675A Fan inlet cone and aviation turbofan engine gas handling system
CN106555619A The control device and method in gas turbine blade gap