US4664134A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Fuel system for flight vehicle
Assignee: Boeing Co
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Filing: 1985-09-30
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Granted: 1987-05-12
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Expires: 2005-09-30
Abstract
Abstract A main storage tank (2) is pressurized by engine bleed air. A supply tank (12) communicates with tank (2) and with an engine feed line (50). A fluid impermeable expandable wall (34) separates tank (12) into isolator chamber (38) and pressure chamber (40). A surface tension screen (44) covers inlet (42) into isolator chamber (38) to allow liquid fuel to enter chamber (38) and prevent gas from entering chamber (38). During operation of the flight vehicle, a fuel pump withdraws fuel from chamber (38). Pressure chamber (40) is vented to ambient air when the flight vehicle is under no power or is operating under g forces greater than zero, to allow wall (34) to expand and contract to compensate for changes in temperature and pressure. Chamber (40) is pressurized by engine bleed air when the vehicle is operating under zero or negative g forces.
Inventors
- 👤 Ronald J. Pera
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-03 02:06
CPC Classifications
F; F02; F02C; F02C7/00; F02C7/22; B; B64; B64D; B64D37/00; B64D37/02; B64D37/14; B64D37/20; B64D37/24; Y; Y10; Y10T; Y10T137/00; Y10T137/0318; Y10T137/0396; Y10T137/0753; Y10T137/2931; Y10T137/3003; Y10T137/3021; Y10T137/8593; Y10T137/86187
Claims Analysis
Total Claims: 14
Claim 1
Independent Claim
210 words
In a flight vehicle fuel system of the type having a storage tank for storing fuel and means for pressurizing the tank, apparatus for compensating for temperature and pressure changes and negative g conditions, and for isolating the fuel from contamination, said apparatus comprising: a fuel supply tank having an inlet communicating with the storage tank, and an outlet communicating with an engine feed line; a fluid impermeable movable wall separating the supply tank into a variable volume fuel isolator chamber and a varible volume pressure chamber, said inlet and said outlet communicating with the isolating chamber; a surface tension screen covering the inlet for allowing liquid fuel to enter the isolator chamber and preventing gas from entering the isolator chamber; and venting and pressurizing means for venting the pressure chamber to ambient air when the vehicle is under no power or is operating under positive g forces, to allow the movable wall to expand and contract to compensate for changes in temperature and pressure, and for pressurizing the pressure chamber when the vehicle is operating under negative g forces, to equalize the pressure on both sides of said wall so that said wall will contract as fuel is drawn out of the isolator chamber into the engine feed line.
Claim 2
Dependent Claim
210 words
In a flight vehicle fuel system of the type having a storage tank for storing fuel and means for pressurizing the tank, apparatus for compensating for temperature and pressure changes and negative g conditions, and for isolating the fuel from contamination, said apparatus comprising: a fuel supply tank having an inlet communicating with the storage tank, and an outlet communicating with an engine feed line; a fluid impermeable movable wall separating the supply tank into a variable volume fuel isolator chamber and a varible volume pressure chamber, said inlet and said outlet communicating with the isolating chamber; a surface tension screen covering the inlet for allowing liquid fuel to enter the isolator chamber and preventing gas from entering the isolator chamber; and venting and pressurizing means for venting the pressure chamber to ambient air when the vehicle is under no power or is operating under positive g forces, to allow the movable wall to expand and contract to compensate for changes in temperature and pressure, and for pressurizing the pressure chamber when the vehicle is operating under negative g forces, to equalize the pressure on both sides of said wall so that said wall will contract as fuel is drawn out of the isolator chamber into the engine feed line.
Claim 3
Dependent Claim
52 words
Apparatus as described in claim 1, in which the means for pressurizing the storage tank communicates the storage tank with a source of pressurized engine bleed air, and the venting and pressurizing means includes valve means for selectively communicating the pressure chamber with ambient air or such source of engine bleed air.
Claim 4
Dependent Claim
67 words
Apparatus as described in claim 1, in which the supply tank includes a base portion defining an auxiliary chamber on the side of the screen opposite the isolator chamber; which further comprises a conduit communicating the storage tank with the auxiliary chamber; and in which the screen and auxiliary chamber are dimensioned to maximize the area of the screen through which fuel may enter the isolator chamber.
Claim 5
Dependent Claim
52 words
Apparatus as described in claim 3, in which the means for pressurizing the storage tank communicates the storage tank with a source of pressurized engine bleed air, and the venting and pressurizing means includes valve means for selectively communicating the pressure chamber with ambient air or such source of engine bleed air.
Claim 6
Dependent Claim
30 words
Apparatus as described in claim 1, in which the screen is positioned below the storage tank so that gas will readily return to the storage tank under positive g conditions.
Claim 7
Dependent Claim
35 words
Apparatus as described in claim 3, in which the auxiliary chamber is positioned above the screen and below the storage tank so that gas will readily return to the storage tank under positive g conditions.
Claim 8
Dependent Claim
211 words
For use in a flight vehicle fuel system of the type having a storage tank for storing fuel and means for pressurizing the tank, a method of compensating for temperature and pressure changes and negative g conditions and of isolating the fuel from contamination, said method comprising: providing a fuel supply tank; dividing the supply tank into a variable volume fuel isolator chamber and a variable volume pressure chamber separated by a fluid permeable movable wall; communicating the isolator chamber with the storage tank through an inlet in the isolator chamber with an engine feed line through an outlet in the isolator chamber; and covering the inlet with a surface tension screen to allow liquid fuel to enter the isolator chamber and prevent gas from entering the isolator chamber; venting the pressure chamber to ambient air when the vehicle is under no power or is operating under positive g forces, to allow the movable wall to expand and contract to compensate for changes in temperature and pressure; and pressurizing the pressure chamber when the vehicle is operating under negative g forces, to equalize the pressure on both sides of said wall so that said wall will contract as fuel is drawn out of the isolator chamber into the engine feed line.
Claim 9
Dependent Claim
211 words
For use in a flight vehicle fuel system of the type having a storage tank for storing fuel and means for pressurizing the tank, a method of compensating for temperature and pressure changes and negative g conditions and of isolating the fuel from contamination, said method comprising: providing a fuel supply tank; dividing the supply tank into a variable volume fuel isolator chamber and a variable volume pressure chamber separated by a fluid permeable movable wall; communicating the isolator chamber with the storage tank through an inlet in the isolator chamber with an engine feed line through an outlet in the isolator chamber; and covering the inlet with a surface tension screen to allow liquid fuel to enter the isolator chamber and prevent gas from entering the isolator chamber; venting the pressure chamber to ambient air when the vehicle is under no power or is operating under positive g forces, to allow the movable wall to expand and contract to compensate for changes in temperature and pressure; and pressurizing the pressure chamber when the vehicle is operating under negative g forces, to equalize the pressure on both sides of said wall so that said wall will contract as fuel is drawn out of the isolator chamber into the engine feed line.
Claim 10
Dependent Claim
53 words
A method as described in claim 7, in which the storage tank is pressurized by communicating it with a source of pressurized engine bleed air, and the step of pressurizing the pressure chamber in the supply tank comprises operating a valve to communicate the pressure chamber with such source of engine bleed air.
Claim 11
Dependent Claim
126 words
A method as described in claim 7, further comprising filling the system in a reverse direction to ensure that no gas is left in the system; said filling including opening a vent in the storage tank, collapsing the movable wall to force gas out of the isolator chamber through the screen and the opened vent in the storage tank, feeding fuel into the isolator chamber through the engine feed line and said outlet and into the storage tank from the isolator chamber through the screen and said inlet, continuing to so feed fuel until fuel exits the opened vent, closing the vent, and removing an amount of fuel from the isolator chamber through said feed line sufficient to allow for expansion and contraction of said wall.
Claim 12
Dependent Claim
28 words
A method as described in claim 7, comprising positioning the screen below the storage tank to facilitate return of gas to the storge tank under positive g conditions.
Claim 13
Dependent Claim
66 words
A method as described in claim 7, in which the step of communicating the isolator chamber with the storage tank comprises providing an auxiliary chamber on the side of the screen opposite the isolator chamber, communicating the auxiliary chamber with the storage tank, and dimensioning the screen and the auxiliary chamber to maximize the area of the screen through which fuel may enter the isolator chamber.
Claim 14
Dependent Claim
33 words
A method as described in claim 11, comprising positioning the auxiliary chamber above the screen and below the storage tank to facilitate return of gas to the stoage tank under positive g conditions.
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USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1990-05-11 | 1990-11-10 | 1991-05-12 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1994-05-11 | 1994-11-10 | 1995-05-12 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1998-05-11 | 1998-11-10 | 1999-05-12 | $7700.00 | Window Closed / Lapsed |