Method of operating a turbine

Claim 2

Method of operating an auxiliary gas turbine which is used for starting an aircraft engine and for driving auxiliary on-board equipment comprising the steps of, generating externally to the turbine a pressurized gas without sustaining combustion, for driving the turbine; mixing the pressurized gas after its generation with aircraft engine fuel; and feeding the mixture to the turbine for driving the turbine, so that the turbine is driven by the mixture without undergoing or having undergone combustion.

Claim 3

Method as in claim 1, wherein the mixing is carried out by fuel injection, not in excess of the amount of fuel which can evaporate upon injection.

Claim 4

Method as in claim 1, wherein the external generation of gas is comprised of the decompositioning of hydrazine.

Claim 5

In a method of operating a gas turbine on board of an aircraft, the turbine having a turbine chamber and a combustion chamber which normally produces propellant gas by combustion, so that the turbine is normally operated by combustion of fuel in the combustion chamber, comprising the steps of decomposing a monocomponent fuel without combustion when combustion does not provide for the development of driving gases for any reason, so as to provide a substitute driving gas for the turbine resulting from the decomposing; mixing the substitute driving gas after its generation with aircraft engine fuel; and feeding the mixture to the turbine chamber, by-passing the combustion chamber, for driving the turbine by the mixture without combustion thereof.

Claim 6

In a method of operating a gas turbine on board of an aircraft, the turbine having a turbine chamber and a combustion chamber which normally produces propellant gas by combustion, so that the turbine is normally operated by combustion of fuel in the combustion chamber, comprising the steps of decomposing a monocomponent fuel without combustion when combustion does not provide for the development of driving gases for any reason, so as to provide a substitute driving gas for the turbine resulting from the decomposing; mixing the substitute driving gas after its generation with aircraft engine fuel; and feeding the mixture to the turbine chamber, by-passing the combustion chamber, for driving the turbine by the mixture without combustion thereof.

Claim 7

In a method as in claim 4, using hydrazine as the mono-component fuel, the engine fuel as mixed therewith evaporating completely before the mixture enters the turbine.

Claim 8

In a method as in claim 4, wherein the mixing is carried out by fuel injection, not in excess of the amount of fuel which can evaporate upon injection.

Claim 9

In a method as in claim 4, wherein the external generation of gas is comprised of the decompositioning of hydrazine.

Claim 10

In a method as in claim 4, using a hydrazine-water mixture as monofuel.