Compressor power unit fuel flow control

Claim 2

Apparatus for supplying fuel to a combustor having a perforated combustion liner circumscribed by an inlet plenum adapted to receive pressurized air from a source thereof, said apparatus comprising: (a) nozzle means for receiving pressurized fuel from a source thereof and injecting the received fuel into the liner; (b) means for supplying fuel to said nozzle means at an essentially constant pressure; (c) means for varying the fuel pressure drop across said nozzle means, to thereby modulate the fuel flow therethrough without appreciably altering the pressure of fuel supplied to said nozzle means; and (d) means for maintaining the absolute pressure ratio between the pressure of fuel supplied to said nozzle means and the pressure within the liner within a range between about 1.1 and about 1.3.

Claim 3

Apparatus for supplying fuel to a combustor having a perforated combustion liner circumscribed by an inlet plenum adapted to receive pressurized air discharged from a compressor, said apparatus comprising: (a) nozzle means for receiving pressurized fuel from a source thereof and injecting the received fuel into the liner; (b) means for supplying fuel to said nozzle means at an essentially constant pressure; and (c) means for varying the fuel pressure drop across said nozzle means, to thereby modulate the fuel flow therethrough without appreciably altering the pressure of fuel supplied to said nozzle means; said varying means (c) comprising means for selectively varying the pressure within the liner, including means for bleeding off a selectively variable quantity of air discharged from the compressor.

Claim 4

Apparatus for supplying fuel to a combustor having a perforated combustion liner circumscribed by an inlet plenum adapted to receive pressurized air discharged from a compressor, said apparatus comprising: (a) nozzle means for receiving pressurized fuel from a source thereof and injecting the received fuel into the liner; (b) means for supplying fuel to said nozzle means at an essentially constant pressure; and (c) means for varying the fuel pressure drop across said nozzle means, to thereby modulate the fuel flow therethrough without appreciably altering the pressure of fuel supplied to said nozzle means; said varying means (c) comprising means for selectively varying the pressure within the liner, including means for bleeding off a selectively variable quantity of air discharged from the compressor.

Claim 5

The apparatus of claim 3 wherein said last-mentioned means include a bleed air duct communicating with said combustion liner, and valve means for modulating flow through said bleed air duct.

Claim 6

A gas turbine engine compressor power unit comprising: (a) rotationally drivable compressor means for receiving, compressing and discharging a flow of air; (b) rotationally drivable turbine means rotationally coupled to said compressor means; (c) combustor means for receiving fuel and pressurized air, mixing and burning the received fuel and air, and discharging hot, expanding gas through said turbine means to rotationally drive the same, said combustor means having a perforated liner circumscribed by an inlet plenum communicating with said compressor to receive compressed air discharged therefrom; (d) nozzle means for receiving pressurized fuel from a source thereof and injecting the fuel into said liner; (e) means for supplying fuel to said nozzle means at an essentially constant pressure; and (f) means for bleeding off a selectively variable quantity of compressor discharge air to thereby modulate the flow of fuel through said nozzle means solely by causing a pressure variation within said liner.

Claim 7

A gas turbine engine compressor power unit comprising: (a) rotationally drivable compressor means for receiving, compressing and discharging a flow of air; (b) rotationally drivable turbine means rotationally coupled to said compressor means; (c) combustor means for receiving fuel and pressurized air, mixing and burning the received fuel and air, and discharging hot, expanding gas through said turbine means to rotationally drive the same, said combustor means having a perforated liner circumscribed by an inlet plenum communicating with said compressor to receive compressed air discharged therefrom; (d) nozzle means for receiving pressurized fuel from a source thereof and injecting the fuel into said liner; (e) means for supplying fuel to said nozzle means at an essentially constant pressure; and (f) means for bleeding off a selectively variable quantity of compressor discharge air to thereby modulate the flow of fuel through said nozzle means solely by causing a pressure variation within said liner.

Claim 8

The compressor power unit of claim 4 further comprising means for maintaining the absolute pressure ratio between said essentially constant fuel supply pressure and the pressure within said liner within a range of from about 1.1. to about 1.3.

Claim 9

The compressor power unit of claim 5 wherein said nozzle means comprise a relatively low pressure fuel injection nozzle.

Claim 10

The compressor power unit of claim 6 wherein said nozzle is an air blast fuel nozzle.

Claim 11

The compressor power unit of claim 4 wherein said bleeding off means (f) comprise a bleed air duct communicating with said inlet plenum, and valve means for selectively varying flow through said bleed air duct.