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XU JINQUAN

Overview
  • Total Patents
    31
  • GoodIP Patent Rank
    219,029
  • Filing trend
    0.0%
About

XU JINQUAN has a total of 31 patent applications. It increased the IP activity by 0.0%. Its first patent ever was published in 1999. It filed its patents most often in United States and China. Its main competitors in its focus markets engines, pumps and turbines, environmental technology and materials and metallurgy are LACY BENJAMIN PAUL, MTU Aero Engines AG and ANSALDO ENERGIA IP UK LTD.

Patent filings in countries

World map showing XU JINQUANs patent filings in countries
# Country Total Patents
#1 United States 25
#2 China 6

Patent filings per year

Chart showing XU JINQUANs patent filings per year from 1900 to 2020

Top inventors

# Name Total Patents
#1 Xu Jinquan 31
#2 Gao Zhanjun 4
#3 Xu Jianyu 3
#4 Zelesky Mark F 3
#5 Levasseur Glenn 3
#6 Gleiner Matthew S 2
#7 Griffin Todd R 2
#8 Yokajty Joseph E 2
#9 Kohli Atul 2
#10 Egan Kevin P 1

Latest patents

Publication Filing date Title
CN109984180A A kind of dish leaf preservation method of dish leaf small curd
CN107389537A A kind of novel multi-channel cell counter and multichannel cell count system
US2015003995A1 Aircraft engine component with locally tailored materials
US2014076661A1 Lubrication system having porous feature
US2014069743A1 Lubrication system having segmented anti-backflow feature
US2013205790A1 Multi-lobed cooling hole and method of manufacture
US2013205803A1 Multi-lobed cooling hole array
US2013205794A1 Gas turbine engine component with impingement and lobed cooling hole
US2013209236A1 Gas turbine engine component with compound cusp cooling configuration
US2013209235A1 Gas turbine engine component with cusped, lobed cooling hole
US2013209229A1 Gas turbine engine component with converging/diverging cooling passage
US2013209233A1 Cooling hole with enhanced flow attachment
US2013209232A1 Multi-lobed cooling holes in gas turbine engine components having thermal barrier coatings
US2013209234A1 Multiple diffusing cooling hole
US2013209228A1 Gas turbine engine component with cusped cooling hole
US2013205801A1 Multi-lobed cooling hole and method of manufacture
US2013205793A1 Gas turbine engine component with impingement and diffusive cooling
US2013209227A1 Gas turbine engine component with diffusive cooling hole
US2013280092A1 Airfoil cooling enhancement and method of making the same
US2013266816A1 Additive manufacturing hybrid core