1. A method of performing multiphase flow measurements in a multiphase flow stream including liquid and gas components, said method comprising:
measuring a mass flow rate and density of said multiphase flow stream using a Coriolis flow meter; and
calculating to quantify flow rates of discrete liquid and gas components, said calculation comprising solving N equations with N unknowns where the measured density is used in the N equations without being compensated based on a gas void calibration of the meter.
2. The method of claim 1 further comprising the steps of:
determining a temperature of said multiphase flow;
determining a pressure of said multiphase flow; and
correcting said flow rate of said discrete liquid component to a standard volume flow rate using said temperature measurement, said pressure, and correlations obtained from an industry standards group.
3. The method of claim 1 further comprising the steps of:
determining a temperature of said multiphase flow;
determining a pressure of said multiphase flow; and
correcting said flow rate of said discrete gas component to a standard volume flow rate using said temperature measurement, said pressure, and correlations obtained from an industry standards group.
4. A multiphase flow stream measurement system for use in flow streams including multiple liquid components and a gas component comprising:
means for measuring a mass flow rate and density of said multiphase flow stream; and
means for measuring a flow rate of said liquid and gas components, wherein said means for measuring a flow rate of said liquid and gas components uses a calculation to quantify flow rates of discrete liquid and gas phases in said multiphase flow stream, said calculation comprising solving N equations with N unknowns where the measured density is used in the N equations without being compensated based on a gas void calibration of the meter.
5. The multiphase flow measurement system of claim 4 wherein said means for measuring a mass flow rate of said multiphase flow stream comprises a mass flowmeter.
6. The multiphase flow measurement system of claim 5 wherein said mass flowmeter is a Coriolis mass flowmeter.
7. The mulitphase flow measurement system of claim 4 further comprising:
means for determining a temperature of said multiphase flow;
means for determining a pressure of said multiphase flow; and
means for correcting said flow rate of said liquid and gas components to a standard volume flow rate using said temperature measurement, said pressure measurement and correlations obtained from an industry standards group.
8. The multiphase flow measurement system of claim 7 wherein said means for determining said temperature is a Coriolis flowmeter and said means for determining said pressure is a pressure transmitter.
9. A mulitphase flow measurement system for performing multiphase flow measurements in flow streams including multiple liquid phases and a gas phase, said multiphase flow measurement system comprising:
a flowmeter configured to receive said multiphase flow and measure a flow rate and a density of said multiphase flow;
a water cut monitor configured to receive said multiphase flow and determine a water cut of said multiphase flow; and
a controller configured to communicate with said flowmeter and said water cut monitor, for measuring a flow rate of said liquid and gas components, wherein said controller uses a calculation to quantify flow rates of discrete liquid and gas phases in said multiphase flow stream, said calculation comprising solving N equations with N unknowns where the measured density is used in the N equations without being compensated based on a gas void calibration of the meter.
10. The multiphase flow measurement system of claim 9 wherein said flowmeter comprises a Coriolis mass flowmeter.
11. The multiphase flow measurement system of claim 9 wherein said flowmeter is configured to measure a temperature of said multiphase flow and said system further comprises:
a pressure transmitter for determining a pressure of said multiphase flow; and
means for correcting said flow rate of said liquid and gas components to a standard volume flow rate using said temperature, said pressure, and correlations obtained from an industry standards group.
The claims below are in addition to those above.
All refrences to claim(s) which appear below refer to the numbering after this setence.
1. A sandwich structure having vibration damping, comprising:
first and second facesheets;
a structural core sandwiched between the first and second facesheets and having a cavity therein; and
vibration damping foam within the cavity for reducing vibration of the panel.
2. The sandwich structure of claim 1, wherein:
the core includes a honeycomb, and
the cavity includes a plurality of honeycomb cells at least partially filled with the damping foam.
3. The sandwich structure of claim 1, further including:
a plurality of vibration damping particles movable within the cavity for reducing vibration of the panel.
4. The sandwich structure of claim 3, wherein the particles include at least one of:
volcanic ash,
plastic,
perlite,
sodium-potassium, and
aluminum-silicate
5. The sandwich structure of claim 1, wherein the foam has a density between approximately 5 and 9 pounds per cubic feet.
6. The sandwich structure of claim 1, wherein the second facesheet is less rigid than the first facesheet and is impregnated with a highly damped epoxy resin.
7. The sandwich structure of claim 1 wherein the foam fills approximately 60 to 90 percent of the cavity.
8. The sandwich structure of claim 1, wherein the structure is configured to form a wing-to-body fairing of a aircraft.
9. A vibration damped aircraft fairing, comprising:
first and second skins;
a honeycomb core sandwiched between the first and second skins and having cells defining a plurality of cavities within the core; and,
a vibration damping filler in the cells for damping vibrations in the fairing, the filler including at least one of a foam and a plurality of individual particles movable when vibrated to dissipate vibrational energy within the fairing.
10. The aircraft fairing of claim 9, wherein the filler fills approximately 60 to 90 percent of the volume of the cells.
11. The aircraft fairing of claim 9, wherein each of the first and second skins are composite laminates.
12. The aircraft fairing of claim 11, wherein the second skin includes a facesheet impregnated with a highly damped epoxy resin.
13. The aircraft fairing of claim 9, wherein the filler both the foam and the plurality of individual particles.
14. The aircraft fairing of claim 9, wherein the individual particles include at least one of:
volcanic ash,
plastic,
perlite,
sodium-potassium, and
aluminum-silicate
15. The aircraft fairing of claim 9, wherein the foam has a density between approximately 5 and 9 pounds per cubic feet.
16. The aircraft fairing of claim 9, wherein the individual particles each has a size in a range of approximately 1 to 300 microns.
17. The aircraft fairing of claim 9, wherein the honeycomb core is formed from at least one of:
aluminum,
Nomex\xae,
metal,
cotton, and
a composite.
18. The aircraft fairing of claim 9, wherein the panel is configured to form a win-to-body fairing.
19. A method of reducing noise in an aircraft cabin caused by vibration of a wing-to-body fairing on the aircraft, comprising:
providing a cavity within the fairing; and
introducing a vibration damping filler into the cavity for dissipating vibration energy in the fairing.
20. The method of claim 19, wherein:
providing a cavity within the fairing includes sandwiching an open cell honeycomb between two skins, and
introducing the damping filler into the cavity includes partially filling the cells of the honeycomb with at least one of a vibration damping foam and a plurality of individual damping particles.
21. The method of claim 20 wherein partially filling the cells includes filling approximately 60 to 90 percent of the volume of the cells.
22. The method of claim 19 wherein introducing the damping filler into the cavity includes partially filling the cells of the honeycomb with both a vibration damping foam and a plurality of individual damping particles.
23. A wing-to-body aircraft fairing having vibrations reduced by the method of claim 19.
24. A vibration damped wing-to-aircraft aircraft fairing, comprising:
first and second laminated composite skins, one of the skins including a facesheet impregnated with a highly damped epoxy resin;
a honeycomb core sandwiched between and bonded to the first and second skins and including a plurality of open cells;
a damping foam partially filling the cells and having a density between approximately 5 and 9 pounds per cubic feet; and,
a plurality of individual damping particles movable within and partially filling the cells,
the particle each having a size between approximately 1 and 300 microns, and including at least one of volcanic ash, plastic, perlite, sodium-potassium, and aluminum-silicate,
the foam and the particles filling between approximately 60 to 90 percent of the volume of the cells.
25. A method of fabricating a wing-to-body aircraft fairing having reduced vibration, comprising:
laying up a composite panel, including sandwiching an open cell honeycomb core between two composite laminate skins and impregnating one of the skins with a high damping resin;
partially filling the cells of the core with vibration damping foam;
partially filling the cells of the core with vibration damping particles;
bonding the core to the skins;
forming the layup over tooling into the shape of a fairing; and,
curing the formed layup.