Propulsion system thermal management
A flying vehicle propulsion system comprises a propulsor, a drive system, a heat exchanger, and a housing in which the heat exchanger is provided. The propulsor produces a propulsor fluid flow. In a first operation configuration of the propulsion system, at least part of the propulsor fluid flow is incident on the exchanger. A propulsor fluid flow inlet port of the housing fluidly communicates with a chamber of the housing on an inlet side of the exchanger. The inlet port receives the propulsor fluid flow for ingestion into the chamber and exchanger and comprises a valve to close the port when the valve is closed and open the port when the valve is open. The valve is biased such that at least one of: the valve opens passively under a propulsor fluid flow rate influence above a pre-defined threshold impinging on the valve; and the valve closes passively under a biasing influence.
1 . A flying vehicle propulsion system comprising:
a propulsor, a drive system and a heat exchanger, wherein the drive system is arranged to drive the propulsor and the heat exchanger is arranged to thermally regulate at least part of the drive system, the propulsor being arranged to move fluid, thereby producing a propulsor fluid flow having a main direction, and wherein:
the flying vehicle propulsion system is arranged such that in a first operation configuration, at least part of the propulsor fluid flow is incident on the heat exchanger, thereby thermally regulating the at least part of the drive system;
the flying vehicle propulsion system further comprises a housing in which the heat exchanger is provided;
the housing comprises a propulsor fluid flow inlet port in fluid communication with a first chamber of the housing on an inlet side of the heat exchanger, the propulsor fluid flow inlet port being arranged to receive the propulsor fluid flow for ingestion into the first chamber and heat exchanger;
the propulsor fluid flow inlet port comprises a valve arranged to close the propulsor fluid flow inlet port when the valve is closed and open the propulsor fluid flow inlet port when the valve is open; and
the valve is biased such that at least one of:
the valve opens passively under an influence of a propulsor fluid flow rate of the propulsor fluid flow above a pre-defined threshold impinging on the valve; and
the valve closes passively under an influence of a biasing force.
2 . The flying vehicle propulsion system according to claim 1 , wherein in a second operation configuration, the propulsion system is arranged such that a ram fluid flow produced by forward flight of a flying vehicle equipped with the propulsion system, is incident on the heat exchanger, thereby thermally regulating the at least part of the drive system.
3 . The flying vehicle propulsion system according to claim 2 , wherein the main direction of the propulsor fluid flow is different from a main direction of the ram fluid flow.
4 . The flying vehicle propulsion system according to claim 3 , wherein the main direction of the propulsor fluid flow is substantially perpendicular to the main direction of the ram fluid flow.
5 . The flying vehicle propulsion system according to claim 2 , wherein the first operation configuration is a configuration in which the ram fluid flow is not present or has a velocity below a predetermined threshold.
6 . The flying vehicle propulsion system according to claim 1 , wherein the housing comprises a ram fluid flow inlet port in fluid communication with the first chamber of the housing on the inlet side of the heat exchanger, the ram fluid flow inlet port being arranged to receive ram fluid flow for ingestion into the first chamber and heat exchanger.
7 . The flying vehicle propulsion system according to claim 6 , wherein the valve, the propulsor fluid flow inlet port and the ram fluid flow inlet port are arranged such that the propulsor fluid flow provides a force tending to open the valve and the ram fluid flow provides a force tending to close the valve.
8 . The flying vehicle propulsion system according with claim 1 , wherein the housing comprises an exit port in fluid communication with a second chamber of the housing on a discharge side of the heat exchanger, the exit port being arranged to exhaust fluid that has passed from the first chamber, through the heat exchanger to the second chamber, out of the housing.
9 . The flying vehicle propulsion system according to claim 8 , wherein the exit port is provided on a side wall of the housing.
10 . The flying vehicle propulsion system according to claim 1 , wherein the heat exchanger is arranged obliquely within the housing.
11 . The flying vehicle propulsion system according to claim 1 , wherein at least part of the drive system is provided within the housing.
12 . The flying vehicle propulsion system according to claim 1 , further comprising a pylon arranged to mount the propulsor to a flying vehicle.
13 . The flying vehicle propulsion system according to claim 1 , wherein the drive system comprises a fuel cell which is at least partially thermally regulated by the heat exchanger.
14 . The flying vehicle propulsion system according to claim 1 , wherein the propulsor is a propeller, rotor, tilt-rotor ducted fan.
15 . The flying vehicle propulsion system according to claim 1 , wherein the heat exchanger is a radiator.
16 . A flying vehicle comprising the flying vehicle propulsion system of claim 1 .
17 . The flying vehicle according to claim 16 , wherein the flying vehicle is arranged for vertical take-off and/or landing and/or short take-off and/or rolling vertical landing with the propulsor providing at least part of the vertical lift force required.
18 . The flying vehicle according to claim 16 , wherein the flying vehicle comprises one or more forward thrust system arranged to provide forward thrust for at least one of taxiing, conventional take-off, short take-off or forward flight.