US3736072A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Systems for the supply of liquid fuel to gas-turbine engines
Assignee: Plessey Handel und Investments AG
•
Filing: 1971-08-24
•
Granted: 1973-05-29
•
Expires: 1991-08-24
Abstract
Abstract To permit the booster pumps in aircraft wing tanks to be switched-off immediately after starting of the engine, thus reducing the fire hazards in the event of a crash, without endangering the maintenance, even at high altitude, of adequate pressure at the inlet 4a of an engine-driven fixed-displacement main fuel pump, the energy of the spill flow is utilized in an injector-type pump to boost the pressure of the fuel in the supply line leading from a backing pump to the main fuel pump. A novel form of injection-type pump is also described which makes use of the Coanda wall-attachment effect.
Inventors
- 👤 H G Turner
- 👤 R Wood
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-24 00:27
CPC Classifications
F; F04; F04C; F04C15/00; F04C15/06; F04C15/062; F02; F02C; F02C7/00; F02C7/22; F02C7/236
Claims Analysis
Total Claims: 7
Claim 1
Independent Claim
242 words
A system for supplying fuel to a gas-turbine engine of an aircraft, which comprises: a fuel tank; a positive-displacement main fuel pump driven at a speed proportional to that of the engine and having an inlet connected to said tank by a fuelintake line, and an outlet leading to said engine; a booster pump arranged in at least close proximity to the tank and operable to raise the pressure energy of liquid fuel entering said line from said tank, said booster pump having driving means independent of the engine; a backing pump included in said line between said booster pump and said main fuel pump for simultaneous operation with the main fuel pump to raise the pressure of liquid fuel entering the main fuel pump from said line; fuel regulator means interposed between said outlet of the engine and operative to return to said intake line the excess of the fuel delivered by said main fuel pump over the momentary fuel requirements of the engine; a jet pump interposed between the backing pump and the inlet of the main fuel pump to raise the pressure of the liquid entering the main fuel pump from the backing pump, said jet pump having a jet inlet arranged to be fed with fuel thus returned by said regulating means and switch-off means operable to deenergise the driving means of the booster pump without affecting the operation of the main fuel pump and the backing pump.
Claim 2
Independent Claim
242 words
A system for supplying fuel to a gas-turbine engine of an aircraft, which comprises: a fuel tank; a positive-displacement main fuel pump driven at a speed proportional to that of the engine and having an inlet connected to said tank by a fuelintake line, and an outlet leading to said engine; a booster pump arranged in at least close proximity to the tank and operable to raise the pressure energy of liquid fuel entering said line from said tank, said booster pump having driving means independent of the engine; a backing pump included in said line between said booster pump and said main fuel pump for simultaneous operation with the main fuel pump to raise the pressure of liquid fuel entering the main fuel pump from said line; fuel regulator means interposed between said outlet of the engine and operative to return to said intake line the excess of the fuel delivered by said main fuel pump over the momentary fuel requirements of the engine; a jet pump interposed between the backing pump and the inlet of the main fuel pump to raise the pressure of the liquid entering the main fuel pump from the backing pump, said jet pump having a jet inlet arranged to be fed with fuel thus returned by said regulating means and switch-off means operable to deenergise the driving means of the booster pump without affecting the operation of the main fuel pump and the backing pump.
Claim 3
Independent Claim
250 words
A system for supplying liquid fuel to a gas turbine engine of an aircraft, which comprises: a fuel tank remote from the engine; a positive-displacement main fuel pump arranged adjacent to the engine and driven at a speed proportional to that of the engine, said main fuel pump having an inlet connected to the said tank by a fuel-intake line, and an outlet leading to said engine; a booster pump arranged in at least close proximity to the tank and operable to raise the pressure of liquid fuel entering said intake line from said tank, said booster pump having driving means independent of the engine; a backing pump arranged in proximity to the main fuel pump for simultaneous operation with the main fuel pump to raise the pressure of liquid fuel entering the main fuel pump from said line; an automatic regulator interposed between said outlet and the engine and operative to divert to a return line the excess of the fuel delivered by the fuel pump over the momentary fuel requirement of the engine; a jet pump interposed between the backing pump and the inlet of the main fuel pump to raise the pressure of the liquid fuel entering the main fuel pump from the backing pump, said jet pump having a jet inlet arranged to form the outlet of said return line; and switch-off means operable to de-energise the driving means of the booster pump without affecting the operation of the main fuel pump and the backing pump.
Claim 4
Independent Claim
250 words
A system for supplying liquid fuel to a gas turbine engine of an aircraft, which comprises: a fuel tank remote from the engine; a positive-displacement main fuel pump arranged adjacent to the engine and driven at a speed proportional to that of the engine, said main fuel pump having an inlet connected to the said tank by a fuel-intake line, and an outlet leading to said engine; a booster pump arranged in at least close proximity to the tank and operable to raise the pressure of liquid fuel entering said intake line from said tank, said booster pump having driving means independent of the engine; a backing pump arranged in proximity to the main fuel pump for simultaneous operation with the main fuel pump to raise the pressure of liquid fuel entering the main fuel pump from said line; an automatic regulator interposed between said outlet and the engine and operative to divert to a return line the excess of the fuel delivered by the fuel pump over the momentary fuel requirement of the engine; a jet pump interposed between the backing pump and the inlet of the main fuel pump to raise the pressure of the liquid fuel entering the main fuel pump from the backing pump, said jet pump having a jet inlet arranged to form the outlet of said return line; and switch-off means operable to de-energise the driving means of the booster pump without affecting the operation of the main fuel pump and the backing pump.
Claim 5
Dependent Claim
38 words
A system as claimed in claim 2, wherein said main fuel pump is dimensioned for a maximum delivery which exceeds only by a safety margin the maximum flow that the automatic fuel regulator permits to reach the engine.
Claim 6
Independent Claim
52 words
A system as claimed in clam 2, wherein the jet pump includes an injection pipe which forms the end of the return line, said injection pipe being arranged to form a jet whose direction substantially coincides with the direction of flow of the fuel entering the jet pump from the fuel-intake line.
Claim 7
Dependent Claim
62 words
A system as claimed in claim 2, wherein the jet pump is of the Coanda type, the fuel coming from the return line being arranged to enter the flow of the fuel coming from the intake line through wall apertures so arranged as to cause the returned fuel to adhere to the walls of the jet pump due to the Coanda effect.
References Cited (Backward Citations)
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1976-05-28 | 1976-11-27 | 1977-05-29 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1980-05-28 | 1980-11-27 | 1981-05-29 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1984-05-28 | 1984-11-27 | 1985-05-29 | $7700.00 | Window Closed / Lapsed |