发明名称 Turbine liquid fuel simulator
摘要 A turbine liquid fuel simulator exposes the components of a liquid fuel system in a turbine engine to the same fuel flows and pressures that the liquid fuel system would endure in an actual startup and run sequence, without burning or otherwise emitting the liquid fuel from the system. A fuel porting mechanism, such as a direction control valve, is installed in each combustor of the turbine engine. The fuel porting mechanism is movable from a first position, wherein liquid fuel is delivered to the combustor nozzle to be burned in normal operation, to a second position, wherein the liquid fuel is diverted to return lines that deliver the liquid fuel back to the fuel tank. To simulate the actual pressures and flows, pressure differential orifices can be installed in the return fuel lines. The orifices includes structures that modify the liquid fuel flow to mimic delivery to the nozzle.
申请公布号 US9354141(B1) 申请公布日期 2016.05.31
申请号 US201414307387 申请日期 2014.06.17
申请人 JANSEN'S AIRCRAFT SYSTEMS CONTROLS, INC. 发明人 McElrath Schuyler V.
分类号 G01M15/14;F02C9/40 主分类号 G01M15/14
代理机构 Ingrassia Fisher & Lorenz, P.C. 代理人 Ingrassia Fisher & Lorenz, P.C.
主权项 1. A turbine liquid fuel simulator for a turbine engine, comprising: one or more fuel porting mechanisms, each fuel porting mechanism being: in fluid communication with a fuel tank of the turbine engine; andin fluid communication with at least one combustion nozzle of the turbine engine; and a liquid fuel return line in fluid communication with each of the fuel porting mechanisms and with the fuel tank; wherein each fuel porting mechanism is configured to switch between: a first position, wherein the fuel porting mechanism directs liquid fuel from the fuel tank to the nozzle, anda second position, wherein the fuel porting mechanism directs the liquid fuel from the fuel tank back to the fuel tank via the liquid fuel return line and prevents liquid fuel from flowing to the nozzle.
地址 Tempe AZ US