초록

An aircraft heating system taps into a bleed air flowpath between a turbine engine and an external bleed air port on the aircraft. A system may be installed as a retrofit for heating the cabin of an aircraft already having a heating system for heating the cockpit.

대표청구항 ▼

1. A heating system for an aircraft comprising:a bleed air conduit along a bleed air flowpath from at least one turbine engine to an external bleed air port on the aircraft separate from the heating system; at least one heating conduit coupled to the bleed air conduit to divert air from the bleed ai

1. A heating system for an aircraft comprising:a bleed air conduit along a bleed air flowpath from at least one turbine engine to an external bleed air port on the aircraft separate from the heating system; at least one heating conduit coupled to the bleed air conduit to divert air from the bleed air flowpath bypassing the external bleed air port; and a heating system outlet in the aircraft cabin and coupled to the at least one heating conduit for discharging diverted air. 2. The heating system of claim 1 wherein the at least one heating conduit is an assembly having:a trunk having an effective cross-sectional area smaller than an effective cross-sectional area of the bleed air conduit; port and starboard branches each having an effective cross-sectional area smaller than the effective cross-sectional area of the trunk; and an electrically controlled valve in or adjacent the trunk for selectively blocking the trunk. 3. The heating system of claim 1 further comprising:an electrically controlled valve coupled to the at least one heating conduit to selectively block and permit flow of the diverted air; and a switch in a cockpit of the aircraft electrically coupled to the valve to control the valve. 4. The heating system of claim 1 further comprising at least one mixing duct and gasper assembly having:a cabin air inlet positioned in the aircraft cabin to draw in cabin air; a bleed air inlet coupled to the at least one heating conduit to receive the diverted air; and a gasper having an inlet receiving a mixture of the cabin air and the diverted air and an outlet defining the heating system outlet, the outlet being manually aimable. 5. The heating system of claim 4 comprising port and starboard such mixing duct and gasper assemblies positioned proximate an aft wall of the cabin and the heating system outlets face essentially forward and the cabin air inlets face essentially laterally outward.6. The heating system of claim 1 wherein the bleed air conduit is located aft of the cabin.7. The heating system of claim 1 in combination with an independent heating system for a cockpit of the aircraft.8. The heating system of claim 1 wherein the at least one turbine engine comprises:an auxiliary power unit; and two main engines, the bleed air flowpath extending from each of the auxiliary power unit and two main engines. 9. The heating system of claim 1 wherein the bleed air port comprises a coupler moiety having a manually-actuated valve.10. The heating system of claim 1 installed in a rotary wing aircraft.11. A method for installing a cabin heating system in an aircraft, the aircraft having at least one turbine engine and a bleed air flowpath from the at least one turbine engine to a bleed air port, the method comprising:at least one of: replacing a conduit having first and second ports along the bleed air flowpath with a replacement conduit having first, second and third ports; and tapping into a conduit having first and second ports along the bleed air flowpath to create a third port; installing a heating conduit network coupled to the third port to draw bleed air from the third port; installing an electrically controlled valve to selectively block and permit flow of the bleed air through the heating conduit network; installing a wiring harness for controlling the electrically controlled valve; and installing a plurality of mixing ducts having first ports for receiving the bleed air and second ports for drawing in cabin air to be mixed with the bleed air. 12. The method of claim 11 wherein either:the installing of the plurality of mixing ducts comprises installing the mixing ducts assembled with respective gaspers; or the method further comprises installing a plurality of gaspers to respective ones of the plurality of mixing ducts. 13. The method of claim 11 further comprising:removing an original heater switch from a cockpit of the aircraft and installing a replacement switch in place of the original switch, the original switch controlling a cockpit heater and the replacement switch controlling the cockpit heater and the cabin heating system at least partially independently. 14. An aircraft heating system kit, comprising:a replacement buddy start tube, having a main inlet port at a proximal end, a main outlet port at a distal end, and a lateral tap port, smaller than the main inlet port and main outlet port; a plurality of conduits for forming a heating conduit assembly for drawing air through the tap port; an electrically controlled valve for selectively blocking and permitting flow of air through the heating conduit assembly; and a mixing duct having a first inlet for receiving air from the heating conduit assembly and a second inlet for drawing in air from the aircraft interior for mixing with the air from the heating conduit assembly. 15. The kit of claim 14 further comprising:a replacement heater switch for mounting in the cockpit; and a wiring harness for coupling the replacement heater switch to the electrically controlled valve. 16. The kit of claim 14 wherein:there are port and starboard such mixing ducts; and the kit further comprises port and starboard gaspers assembled to the respective port and starboard mixing ducts. 17. The kit of claim 15 wherein:the replacement heater switch has positions for at least partially independently controlling a cockpit heater and a cabin heating system. 18. The method of claim 11 comprising said tapping.19. The method of claim 11 comprising said replacing and wherein:said conduit has only first and second ports. 20. The method of claim 11 performed on an aircraft wherein said aircraft has not previously had a bleed air cabin heating system.