Device and process for heating an aircraft cabin
View Patent ↗The invention relates to a device ( 10 ) for heating an aircraft cabin and comprises a first hot air supply line ( 12 ) that leads to an air conditioning unit ( 14 ), a flow control valve ( 16 ) that is disposed in the first hot air supply line ( 12 ) upstream from the air conditioning unit ( 14 ), and a second hot air supply line ( 18 ) that branches off from the first hot air supply line ( 12 ) between the flow control valve ( 16 ) and the air conditioning unit ( 14 ) and bypasses the air conditioning unit ( 14 ). In order to assure air conditioning of the aircraft cabin in the event of a failure of the air conditioning unit ( 14 ) a third hot air supply line ( 20 ) branches off from the first hot air supply line ( 12 ) upstream from the flow control valve ( 16 ), which third hot air supply line ( 20 ) connects the first hot air supply line ( 12 ) to the second hot air supply line ( 18 ). Further a first close off mechanism is disposed in the second hot air supply line ( 18 ) upstream from the junction with the third hot air supply line ( 20 ), which first close off mechanism in its closed position prevents a flow from the second hot air supply line ( 18 ) back into the first hot air supply line ( 12 ). Finally a second close off mechanism is disposed in the third hot air supply line ( 20 ) upstream from the junction with the second hot air supply line ( 18 ).
1. Device ( 10 ) for heating an aircraft cabin, comprising:
a first hot air supply line ( 12 ) leading to an air conditioning unit ( 14 ) for supplying hot air thereto;
a flow control valve ( 16 ) that throttles the volume of hot air to the air conditioning unit ( 14 ), the flow control valve ( 16 ) disposed in the first hot air supply line ( 12 ) upstream from the air conditioning unit ( 14 );
a second hot air supply line ( 18 ) branching off from the first hot air supply line ( 12 ) between the flow control valve ( 16 ) and the air conditioning unit ( 14 ), bypassing the air conditioning unit ( 14 ) and connecting to a downstream end of the air conditioning unit ( 14 ) so as to enable mixing of the hot air supplied via the second hot air supply line ( 18 ) with cool air flowing out of the air conditioning unit ( 14 ) prior to delivery of the air to the aircraft cabin;
a control device ( 28 ) adapted to adjust the mixing of the hot air supplied via the second hot air supply line ( 18 ) and the cool air flowing out of the air conditioning unit ( 14 ) so as to achieve a controlled cabin air temperature, during a normal mode of operation;
a third hot air supply line ( 20 ) branching off from the first hot air supply line ( 12 ) upstream from the flow control valve ( 16 ) and connecting to the second hot air supply line ( 18 ) upstream of where the hot air supplied via the second hot air supply line ( 18 ) mixes with cool air flowing out of the air conditioning unit ( 14 );
a first close off mechanism ( 24 ) disposed in the second hot air supply line ( 18 ) upstream from the junction with the third hot air supply line ( 20 ), the first close off mechanism ( 24 ) operable to, when in a closed position, prevent a flow from the third hot air supply line ( 20 ) and the second hot air supply line ( 18 ) back to the first hot air supply line ( 12 );
a second close off mechanism ( 22 ) disposed in the third hot air supply line ( 20 ) upstream from the junction with the second hot air supply line ( 18 ) and operable to close off the third hot air supply line ( 20 ) during the normal mode of operation and to open the third hot air supply line ( 20 ) if the air conditioning unit ( 14 ) fails; and
an ambient air inlet flap ( 30 ) connected to one of the second or third hot air supply lines ( 18 , 20 ) upstream of the aircraft cabin and adapted to feed cold ambient air for mixing with the hot air supplied via the third hot air supply line ( 20 ), when the air conditioning unit ( 14 ) fails,
wherein the control device ( 28 ) is also adapted to adjust the mixing of the hot air supplied via the third hot air supply line ( 20 ) and the cold ambient air supplied by the ambient air inlet flap ( 30 ) when the air conditioning unit ( 14 ) fails, so as to achieve the controlled air cabin temperature.
2. Device according to claim 1 , wherein the first close off mechanism ( 24 ) assumes its open position and the second close off mechanism ( 22 ) assumes its closed position during a normal mode of operation.
3. Device according to claim 1 , wherein the flow control valve ( 16 ) and the first close off mechanism ( 24 ) assume their closed positions and the second close off mechanism ( 22 ) assumes its open position during a failure of the air conditioning unit ( 14 ).
4. Device according to claim 1 , further comprising
a plurality of first hot air supply lines ( 12 ) leading to a plurality of respective air conditioning units ( 14 );
a flow control valve ( 16 ) in each first hot air supply line ( 12 );
a plurality of second hot air supply lines ( 18 ), each second hot air supply line ( 18 ) branching off from the respective first hot air supply line ( 12 ) between the respective flow control valve ( 16 ) and the air conditioning unit ( 14 ) to bypass the associated air conditioning unit ( 14 ), so as to enable mixing of hot air supplied via the respective second hot air supply line ( 18 ) with air cooled by the air conditioning unit 14 ;
a plurality of third hot air supply lines ( 20 ), each third hot air supply line ( 20 ) branching off the respective first hot air supply line ( 12 ) upstream of the respective flow control valve ( 16 ) and coupled to the associated second hot air supply line ( 18 ) upstream of where the hot air supplied via the second hot air supply line ( 18 ) mixes with air cooled by the air conditioning unit ( 14 );
a plurality of first close off mechanisms ( 24 ), each first close off mechanism ( 24 ) in a respective second hot air supply line ( 18 ) upstream from the junction with the associated third hot air supply line ( 20 ); and
a plurality of second close off mechanisms ( 22 ), each second close off mechanism ( 22 ) in a respective third hot air supply line ( 20 ) upstream from the junction with the associated second hot air supply line ( 18 ).
5. Device according to claim 1 , wherein the first close off mechanism is a non-return valve ( 24 ).
6. Device according to claim 1 , wherein the second close off mechanism is a stop valve ( 22 ).
7. Device according to claim 6 , wherein the stop valve ( 22 ) is automatically actuated.
8. Device according to claim 7 , wherein the stop valve ( 22 ) is connected to the control device ( 28 ).
9. Method for heating an aircraft cabin, comprising:
guiding a controlled flow of hot air from a hot air source via a first hot air supply line ( 12 ) and then through an air conditioning unit ( 14 );
throttling the volume of hot air to the air conditioning unit ( 14 ) using a flow control valve ( 16 );
directing a portion of the controlled flow of hot air from the hot air source via a second hot air supply line ( 18 ), the second hot air supply line ( 18 ) branching from the first hot air supply line ( 12 ) downstream of the flow control valve ( 16 ) but upstream from the air conditioning unit ( 14 ), the portion being directed to bypass the air conditioning unit ( 14 ) and mix with cool air flowing out of a downstream end of the air conditioning unit ( 14 ) during a normal mode of operation;
adjusting, via a control device ( 28 ), the mixing of the hot air supplied via the second hot air supply line ( 18 ) and the cool air flowing out of the air conditioning unit ( 14 ), thereby to achieve the required cabin air temperature during a normal mode of operation;
supplying hot air via a third hot air supply line ( 20 ) that branches off the first hot air supply line ( 12 ) upstream of the flow control valve ( 16 ) and connects to the second hot air supply line ( 18 ) upstream of where the hot air supplied via the second hot air supply line ( 18 ) mixes with cool air flowing out of the air conditioning unit ( 14 ), thereby to bypass the air conditioning unit ( 14 ) and the flow control valve ( 16 ) in the event of a failure of the air conditioning unit ( 14 );
supplying cold ambient air via an ambient air inlet flap ( 30 ) connected to one of the second or third hot air supply lines ( 18 , 20 ) upstream of the aircraft cabin in the event of a failure of the air conditioning unit ( 14 ); and
adjusting, via the control device ( 28 ), the mixing of the hot air supplied via the third hot air supply line ( 20 ) with the cold ambient air supplied via the ambient air inlet flap ( 30 ), thereby to achieve the required cabin air temperature when the air conditioning unit ( 14 ) fails.