When a bi-propellant liquid rocket engine receives a command to shut down,
will the fuel gets cut off first and then the oxidiser - a fuel lean cutoff?
Will the oxidiser gets cut off first and then the fuel - a fuel rich cut off?
Which shut down mode is preferred and for what reasons(like safety, damage to engine,etc)?
Will the mode differ between static engine testing vs during flight?
Will the mode of cut off depend when a turbine is used to induce propellant flow vs a pressure fed case?