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US 11,305,878 B2Granted
Aircraft with environmental control system
AssigneeGE Aviation Systems LLC
InventorsDominique Patrick Sautron, Julian Alexander Opificius
Life of this patent
Estimating the term…
Abstract
An aircraft includes an environmental control system having a bleed air inlet, a gas turbine engine having a low pressure bleed air supply and a high pressure bleed air supply, and a turbo air cycle machine. The turbo air cycle machine includes a compressor fluidly coupled to the low pressure bleed air supply, as well as a turbine fluidly coupled to at least one of the low pressure bleed air supply or the high pressure bleed air supply.
Claims13
An aircraft comprising:
- an environmental control system having a bleed air inlet;
- a gas turbine engine having a low pressure bleed air supply and a high pressure bleed air supply;
- a turbo air cycle machine having rotationally coupled turbine and compressor sections;
- a controllable valve assembly configured to selectively fluidly couple the low pressure bleed air supply to the compressor section, the low pressure bleed air supply to the turbine section, and the high pressure bleed air supply to the turbine section;
- and
- a turbo-ejector fluidly combining fluid outputs from the turbine and compressor sections into a common flow that is supplied to the bleed air inlet of the environmental control system,
- wherein the low pressure bleed air supply includes a first low pressure bleed air supply directly fluidly coupled to the compressor section and a second low pressure bleed air supply fluidly coupling the first low pressure bleed air supply to the high pressure bleed air supply,
- wherein the controllable valve assembly further comprises:
- a first controllable valve provided along the first low pressure bleed air supply upstream of the second low pressure bleed air supply;
- a second controllable valve provided along the high pressure bleed air supply;
- and
- a check valve provided along the second low pressure bleed air supply.
9 more elements
An aircraft comprising:
- an environmental control system having a bleed air inlet;
- a gas turbine engine having a low pressure bleed air supply and a high pressure bleed air supply;
- a turbo air cycle machine fluidly coupled to the bleed air inlet and comprising:
- a compressor selectively fluidly coupled to the low pressure bleed air supply and having a compressor outlet emitting a compressed air stream;
- and
- a turbine selectively fluidly coupled the low pressure air supply and selectively fluidly coupled to the high pressure bleed air supply and having a turbine outlet emitting a cooled air stream;
- and
- a turbo-ejector fluidly coupled to the compressor outlet and the turbine outlet,
- wherein the low pressure bleed air supply includes a first low pressure bleed air supply directly fluidly coupled to the compressor and a second low pressure bleed air supply fluidly coupling the first low pressure bleed air supply to the high pressure bleed air supply,
- wherein the aircraft further comprises a controllable valve assembly upstream of the turbo air cycle machine and configured to selectively fluidly couple the first low pressure bleed air supply to the compressor and the second low pressure bleed air supply, and the high pressure bleed air supply to the turbine, and
- wherein the controllable valve assembly comprises:
- a first controllable valve provided along the first low pressure bleed air supply upstream of the second low pressure bleed air supply;
- a second controllable valve provided along the high pressure bleed air supply;
- and
- a check valve provided along the second low pressure bleed air supply.
12 more elements
Dependencies are inferred from the claim text.