Ejector-driven fuel stabilization system
View Patent ↗A fuel stabilization unit includes a fuel inlet and outlet, an oxygen permeable membrane and a vacuum source. The vacuum source employs an ejector and a high pressure fluid to generate an oxygen partial pressure differential across the membrane. A fuel deoxygenation system includes a fuel stabilization unit and a vacuum source. The fuel stabilization unit has a fuel flow path, a vacuum chamber and an oxygen permeable membrane separating the fuel flow path and the vacuum chamber. The vacuum source employs an ejector and a high pressure fluid to reduce pressure in the vacuum chamber to generate an oxygen partial pressure differential across the oxygen permeable membrane. A method for deoxygenating a fuel includes delivering a high pressure fluid to an ejector, generating an oxygen partial pressure differential across an oxygen permeable membrane using only the ejector and removing oxygen from the fuel using the oxygen partial pressure differential.
1. A fuel stabilization unit comprising:
an oxygen permeable membrane;
a fuel passage on a side of the membrane;
a chamber on an other side of the membrane;
a venturi effect ejector coupled to the chamber and having an area ratio between about 0.05 and about 0.2 of an area of a suction oxygen flow opening in the ejector to an area of an opening that permits the motive fluid flow in the ejector from the high pressure fluid source, and wherein the ejector is a first vacuum source and a secondary vacuum source is not coupled to the chamber;
a high pressure fluid source for providing high pressure fluid as a motive fluid to the ejector to generate a vacuum in the chamber to generate an oxygen partial pressure differential across the membrane for fuel deoxygenation, the high pressure fluid source selected from the group consisting of fluid bled from a fan of a gas turbine engine, fluid bled from a compressor of a gas turbine engine and combinations thereof; and
a valve positioned between the oxygen permeable membrane and the ejector and configured to regulate the oxygen partial pressure differential across the oxygen permeable membrane;
a temperature sensor for monitoring temperature of fuel in the fuel passage;
a pressure sensor for monitoring the oxygen partial pressure differential; and
a control system for operating the valve based on inputs received from the temperature sensor and the pressure sensor.
2. The fuel stabilization unit of claim 1 , wherein the chamber is a vacuum chamber.
3. The fuel stabilization unit of claim 1 , wherein the oxygen permeable membrane contains tetrafluoroethylene.
4. The fuel stabilization unit of claim 1 , wherein the ejector has an area ratio of about 0.1.
5. The fuel stabilization unit of claim 1 , wherein the ejector area ratio is between 0.05 and 0.2 to allow for a low motive air flow rate between 0.001 kg/s (0.002 pound mass per second) and 0.1 kg/s (0.2 pound mass per second) to eliminate the need for a secondary vacuum source.
6. A fuel deoxygenation system comprising:
a fuel stabilization unit comprising:
a fuel flow path comprising:
a fuel inlet; and
a fuel outlet;
a vacuum chamber; and
an oxygen permeable membrane separating the fuel flow path and the vacuum chamber;
a vacuum source for reducing pressure in the vacuum chamber to generate an oxygen partial pressure differential across the oxygen permeable membrane, wherein the vacuum source consists of an ejector having an area ratio between about 0.05 and about 0.2 and a high pressure fluid source;
a valve positioned between the oxygen permeable membrane and the ejector and configured to regulate the oxygen partial pressure differential across the oxygen permeable membrane;
a temperature sensor for monitoring temperature of fuel in the fuel stabilization unit;
a pressure sensor for monitoring the oxygen partial pressure differential; and
a control system for operating the valve based on inputs received from the temperature sensor and the pressure sensor.
7. The fuel deoxygenation system of claim 6 , wherein the oxygen permeable membrane contains tetrafluoroethylene.
8. The fuel deoxygenation system of claim 6 , wherein the ejector has an area ratio of about 0.1.
9. The fuel deoxygenation system of claim 6 , wherein the vacuum source reduces the pressure in the vacuum chamber to between about 2.0 kPa (15 torr) and about 6.7 kPa (50 torr).
10. The fuel deoxygenation system of claim 6 , wherein the high pressure fluid source is a fan of a gas turbine engine.
11. The fuel deoxygenation system of claim 6 , wherein the high pressure fluid source is a compressor of a gas turbine engine.
12. The fuel deoxygenation system of claim 6 , further comprising:
a throttle valve to regulate fluid flow from the high pressure fluid source.
13. The fuel deoxygenation system of claim 6 , wherein the ejector is coupled to the chamber, wherein a secondary vacuum source is not coupled to the chamber.
14. The fuel deoxygenation system of claim 11 , wherein the ejector is coupled to the chamber, wherein a secondary vacuum source is not coupled to the chamber.
15. A method for deoxygenating a fuel, the method comprising:
delivering a high pressure fluid to an ejector;
generating an oxygen partial pressure differential across an oxygen permeable membrane in contact with the fuel using the ejector and without a secondary vacuum source;
operating a valve positioned between the oxygen permeable membrane and the ejector based on inputs received from a temperature sensor for monitoring temperature of the fuel and a pressure sensor for monitoring the oxygen partial pressure differential, the valve configured to regulate the oxygen partial pressure differential across the oxygen permeable membrane; and
removing oxygen from the fuel using the oxygen partial pressure differential.
16. The method of claim 15 , wherein the ejector has an area ratio between about 0.05 and about 0.2.
17. The method of claim 16 , wherein the high pressure fluid delivered to the ejector has a flow rate between about 0.001 kg/s and about 0.1 kg/s.
18. The method of claim 16 , wherein a ratio of motive flow through the ejector to vacuum flow through the ejector is less than about 0.3.
19. The fuel deoxygenation system of claim 13 , wherein the ejector area ratio is between 0.05 and 0.2 to allow for a low motive air flow rate between 0.001 kg/s (0.002 pound mass per second) and 0.1 kg/s (0.2 pound mass per second) to eliminate the need for a secondary vacuum source.