The United States of America as represented by the Secretary of the Air Force
대리인 / 주소
Singer, Donald J.Scearce, Bobby D.
인용정보
피인용 횟수 :
0인용 특허 :
3
초록▼
A device for measuring fuel flow to a power plant such as a turbo fan engine with a very high degree of accuracy, for example, ±0.5%. A tubular flow loop having quick disconnect fittings for detachably connecting the loop between the aircraft fuel system outlet and the engine fuel inlet is disclosed
A device for measuring fuel flow to a power plant such as a turbo fan engine with a very high degree of accuracy, for example, ±0.5%. A tubular flow loop having quick disconnect fittings for detachably connecting the loop between the aircraft fuel system outlet and the engine fuel inlet is disclosed. Two specially calibrated mass flow transmitters are arranged in series, each preceded by a straight section of piping having a preferred given length to diameter ratio. Preceding each of the two straight pipe sections is a honeycomb flow straightener and three in-series perforated plates for removing any effects of upstream flow characteristics from the transmitters.
대표청구항▼
1. A flow measurement device comprising in combination: a flow path, a mass flow transmitter disposed in said flow path, and means for altering a pattern of fluid flow in a section of said flow path immediately preceding said transmitter, whereby fluid entering said transmitter is substantiall
1. A flow measurement device comprising in combination: a flow path, a mass flow transmitter disposed in said flow path, and means for altering a pattern of fluid flow in a section of said flow path immediately preceding said transmitter, whereby fluid entering said transmitter is substantially constant in flow rate and uniform in character to provide accurate flow measurement. 2. The device of claim 1 wherein said altering means includes a flow straightener preceding said mass flow transmitter including a corrugated material rolled into a spiral disposed in said flow path. 3. The device of claim 2 wherein said corrugated spiral is held in a fixed position in said flow path. 4. The device of claim 2 including at least one perforated plate downstream from said altering means for further fluid flow conditioning, said perforated plate interposed between said mass flow transmitter and said altering means. 5. The device of claim 4 wherein two said perforated plates are provided between said altering means and said flow transmitter, one said perforated plate spaced from the other to define a mixing chamber therebetween. 6. The device of claim 5 wherein three said perforated plates are provided, said third plate spaced from said first and second plates to define two mixing chambers. 7. A device for assisting in trimming fuel flow in an aircraft engine or the like by monitoring fuel mass flow rate just prior to introduction into the engine comprising in combination: a flow loop provided with means for removeable connection to an existing engine fuel line so that said flow loop is interposed in said fuel line, fuel flow measuring means in said loop reflecting fuel mass flow rate admitted to the engine to aid in engine trimming, and means for standardizing fuel flow characteristics upstream said fuel flow measuring means. 8. The device of claim 7 wherein said standardizing means includes a flow straightener preceding said mass flow transmitter including a corrugated material rolled into a spiral disposed in said flow path. 9. The device of claim 8 wherein said corrugated spiral is held in a fixed position in said flow path. 10. The device of claim 8 including at least one perforated plate downstream from said standardizing means for further fluid flow conditioning, said perforated plate interposed between said mass flow transmitter and said standardizing means. 11. The device of claim 10 wherein two said perforated plates are provided between said standardizing means and said flow transmitter, one said perforated plate spaced from the other to define a mixing chamber therebetween. 12. The device of claim 11 wherein three said perforated plates are provided, said third plate spaced from said first and second plate to define two mixing chambers. 13. In a fuel trimming device for an engine: display means adjacent the engine reflecting engine mass flow rate and means operatively connected to said display means and removably connected to a source of fuel supplied to and immediately preceding the engine for monitoring the mass flow rate. 14. In the fuel trimming device of claim 13 wherein said means for monitoring the mass flow rate includes a flow path, a mass flow transmitter disposed in said flow path, and means for altering a pattern of fluid flow in a section of said flow path immediately preceding said transmitter, whereby fluid entering said transmitter is substantially constant in flow rate and uniform in character to provide accurate flow measurement. 15. The device of claim 14 wherein said altering means includes a flow straightener preceding said mass flow transmitter including a corrugated material rolled into a spiral disposed in said flow path. 16. The device of claim 15 wherein said corrugated spiral is held in a fixed position in said flow path. 17. The device of claim 15 including at least one perforated plate downstream from said altering means for further fluid flow conditioning, said perforated plate interposed between said mass flow transmitter and said altering means. 18. The device of claim 17 wherein two said perforated plates are provided between said altering means and said flow transmitter, one said perforated plate spaced from the other to define a mixing chamber therebetween. 19. The device of claim 18 wherein three said perforated plates are provided, said third plate spaced from said first and second plate to define two mixing chambers. 20. A method for trimming an aircraft engine with respect to fuel use including the steps of: interposing a flow loop in the normal fuel flow path to the engine, providing the flow loop with a pair of flow measuring devices, standardizing the flow rate and characteristics of fuel upstream each flow measuring device, averaging the reading of the pair periodically, and displaying the obtained average. 21. The method of claim 20 including determining the difference between the readings of each of the flow measuring devices and displaying the difference between the pair when the average of the pair is being displayed. 22. The method of claim 21 including initially testing the calibration of the flow measuring devices for accuracy. 23. The method of claim 22 including correcting the reading of the mass flow measuring devices for temperature. 24. The device of claim 6 wherein said flow path is of substantially U-shaped configuration including first and second legs, a bight portion therebetween, distal ends of said legs remote from said bight portion provided with means for removably fastening said flow path to the fluid and a second said flow straightener preceding a second said transmitter both provided in said second leg. 25. The device of claim 12 wherein said flow loop is of substantially U-shaped configuration including first and second legs, a bight portion therebetween, distal ends of said legs remote from said bight portion provided with means for removably fastening said flow loop to the fuel and a second said flow straightener preceding a second said transmitter both provided in said second leg. 26. The device of claim 19 wherein said flow path is of substantially U-shaped configuration including first and second legs, a bight portion therebetween, distal ends of said legs remote from said bight portion provided with means for removably fastening said flow path to the fuel and a second said flow straightener preceding a second said transmitter both provided in said second leg. 27. The device of claim 26 wherein said bight portion includes temperature sensing means coupled to said transmitter for biasing and means along the flow path for fluid drawing. 28. The device of claim 25 wherein said bight portion includes temperature sensing means coupled to said transmitter for biasing and means along the flow loop for fuel drawing. 29. The device of claim 24 wherein said bight portion includes temperature sensing means coupled to said transmitter for biasing and means along the flow path for fuel drawing. 30. A mounting bracket for a fuel flow measuring device comprising in combination: first and second portions, means for interconnecting said portions said first portion of inverted U-shaped configuration including means for depending from an aircraft structure, said second portion including shackle means for constraining said device thereto. 31. The device of claim 6 including a mounting bracket for a fuel flow measuring device comprising in combination: first and second portions, means for interconnection said portions, said first portion of inverted U-shaped configuration including means for depending from an aircraft structure, said second portion including shackle means for constraining said device thereto. 32. The device of claim 12 including a mounting bracket for a fuel flow measuring device comprising in combination: first and second portions, means for interconnecting said portions, said first portion of inverted U-shaped configuration including means for depending from an aircraft structure, said second portion including shackle means for constraining said device thereto. 33. The device of claim 19 including a mounting bracket for a fuel flow measuring device comprising in combination: first and second portions, means for interconnecting said portions, said first portion of inverted U-shaped configuration including means for depending from an aircraft structure, said second portion including shackle means for constraining said device thereto.
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이 특허에 인용된 특허 (3)
Bellinga Hendrik (Roden NLX), Device for improving the flow profile in a gas line.
Newman Virgil H. (Washington IL) Tidaback Frank W. (Pekin IL) Jacobson Wayne D. (Peoria IL) Hoagland Donald D. (Peoria IL), Method and apparatus for measuring fuel flow.
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