초록 ▼

The cost of fuel injection nozzles 50 and their tendency to clog in a gas turbine having an annular combustor 26 can be reduced by alternating the fuel injection nozzles 50 with bender jets 56 configured to introduce a combustion supporting gas into an annular combustion zone 40 at locations between

The cost of fuel injection nozzles 50 and their tendency to clog in a gas turbine having an annular combustor 26 can be reduced by alternating the fuel injection nozzles 50 with bender jets 56 configured to introduce a combustion supporting gas into an annular combustion zone 40 at locations between the fuel injectors 50 to achieve uniform turbine inlet temperature distribution while requiring fewer of the nozzles 50 and allowing those nozzles 50 that are utilized to have larger fluid flow paths that are less prone to clogging.

대표청구항 ▼

A gas turbine comprising: a rotor including compressor blades and turbine blades; an inlet adjacent one side of said compressor blades; a diffuser adjacent the other side of said compressor blades; a nozzle adjacent said turbine blades for directing hot gasses at said turbine blades to cause rotatio

A gas turbine comprising: a rotor including compressor blades and turbine blades; an inlet adjacent one side of said compressor blades; a diffuser adjacent the other side of said compressor blades; a nozzle adjacent said turbine blades for directing hot gasses at said turbine blades to cause rotation of said rotor; and an annular combustor about said rotor and having an outlet connected to said nozzle and a primary combustion annulus remote from said outlet, a plurality of fuel injectors to said primary combustion annulus and being substantially equally angular spaced therearound and configured to inject fuel into said primary combustion annulus in a nominally tangential direction and at least an equal number of combustion supporting gas jets located about said primary combustion annulus in alternating relation with said fuel injectors, said jets being configured to introduce a combustion supporting gas into said primary combustion annulus in a nominally tangential direction, combustion supporting gas from said jets uniformly distributing burning fuel about said annulus to thereby enable the use of fewer fuel injectors while avoiding the presence of hot spots.