초록 ▼

An environmental control system (ECS) for an aircraft may be employed to regulate temperature of air entering a cabin of the aircraft. During conditioning of the air, condensate may form in the air. A multiple-stage condensate extraction unit may be incorporated into the ECS to remove the condensat

An environmental control system (ECS) for an aircraft may be employed to regulate temperature of air entering a cabin of the aircraft. During conditioning of the air, condensate may form in the air. A multiple-stage condensate extraction unit may be incorporated into the ECS to remove the condensate. The extraction unit may be provided with two fluid collection stages built into a cylindrical duct. The duct may have a bend therein. One of the collection stages may be positioned on an upstream side of the bend while the second one of the stages may be positioned on a downstream side thereof. The combination of the two stages and their positioning on either side of the bend may provide a particularly compact and efficient condensate extraction unit.

대표청구항 ▼

We claim: 1. An environmental control system for an aircraft comprising: a heat exchanger unit; a fluid extraction unit adapted to receive air from the heat exchanger unit and extract condensate from the air, the fluid extraction unit comprising: an upstream end positioned to receive the air; a dow

We claim: 1. An environmental control system for an aircraft comprising: a heat exchanger unit; a fluid extraction unit adapted to receive air from the heat exchanger unit and extract condensate from the air, the fluid extraction unit comprising: an upstream end positioned to receive the air; a downstream end positioned to deliver the air to a transfer duct for delivery to the heat exchanger unit; a gas stream constraining passageway interconnecting the upstream end and the downstream end of the fluid extraction unit; the passageway having a longitudinal segment and a non-linear gas stream deflection segment; a first fluid collection stage comprising; the longitudinal segment: a swirl device positioned at an upstream end of the longitudinal segment; and a first fluid collector positioned at a downstream end of the longitudinal segment; a second fluid collection stage positioned downstream from the first fluid collection stage and comprising; a gas stream deflection segment; and a second fluid collector positioned at a downstream end of the gas-stream deflection segment for collecting fluid coalesced in the gas stream deflection segment. 2. The apparatus of claim 1 wherein the gas stream experiences a pressure drop no greater than about 2% to about 4% as it passes through the fluid extraction unit. 3. The apparatus of claim 1 wherein the heat exchanger unit comprises: a first inlet port adapted to receive processed air from an engine of the aircraft; a first outlet port to deliver the air to an expansion turbine. a second inlet port to receive the air from the expansion turbine; and a second outlet port for delivering the air to an aircraft cabin. 4. The apparatus of claim 1 which further comprises: a transfer duct positioned near the downstream end of the fluid extraction unit; a gap between the gas stream constraining passageway and an inlet end of the transfer duct; the second fluid collector surrounding the gap; the second fluid collector comprising a plurality of fluid exit ports; and wherein the fluid exit ports are canted downwardly with respect to the direction of level flight of the aircraft whereby at least one of the fluid exit ports will be oriented to allow gravitationally aided fluid flow therethrough irrespective of orientation of the aircraft. 5. The apparatus of claim 4 wherein the fluid exit ports are canted downwardly at an angle of about 20° to about 90°.