Pressure Pressure Atmospheric Pressure
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Che 253M Experiment No. 2 COMPRESSIBLE GAS FLOW
Rev. 8/15 AD/GW ChE 253M Experiment No. 2 COMPRESSIBLE GAS FLOW The objective of this experiment is to familiarize the student with methods for measurement of compressible gas flow and to study gas flow under subsonic and supersonic flow conditions. The experiment is divided into three distinct parts: (1) Calibration and determination of the critical pressure ratio for a critical flow nozzle under supersonic flow conditions (2) Calculation of the discharge coefficient and Reynolds number for an orifice under subsonic (non- choked) flow conditions and (3) Determination of the orifice constants and mass discharge from a pressurized tank in a dynamic bleed down experiment under (choked) flow conditions. The experimental set up consists of a 100 psig air source branched into two manifolds: the first used for parts (1) and (2) and the second for part (3). The first manifold contains a critical flow nozzle, a NIST-calibrated in-line digital mass flow meter, and an orifice meter, all connected in series with copper piping. The second manifold contains a strain-gauge pressure transducer and a stainless steel tank, which can be pressurized and subsequently bled via a number of attached orifices. A number of NIST-calibrated digital hand held manometers are also used for measuring pressure in all 3 parts of this experiment. Assorted pressure regulators, manual valves, and pressure gauges are present on both manifolds and you are expected to familiarize yourself with the process flow, and know how to operate them to carry out the experiment. A process flow diagram plus handouts outlining the theory of operation of these devices are attached. -
Aspects of Flow for Current, Flow Rate Is Directly Proportional to Potential
Vacuum technology Aspects of flow For current, flow rate is directly proportional to potential difference and inversely proportional to resistance. I = V/R or I = V/R For a fluid flow, Q = (P1-P2)/R or P/R Using reciprocal of resistance, called conductance, we have, Q = C (P1-P2) There are two kinds of flow, volumetric flow and mass flow Volume flow rate, S = vA v – the average bulk velocity, A the cross sectional area S = V/t, V is the volume and t is the time. Mass flow rate is S x density. G = vA or V/t Mass flow rate is measured in units of throughput, such as torr.L/s Throughput = volume flow rate x pressure Throughput is equivalent to power. Torr.L/s (g/cm2)cm3/s g.cm/s J/s W It works out that, 1W = 7.5 torr.L/s Types of low 1. Laminar: Occurs when the ratio of mass flow to viscosity (Reynolds number) is low for a given diameter. This happens when Reynolds number is approximately below 2000. Q ~ P12-P22 2. Above 3000, flow becomes turbulent Q ~ (P12-P22)0.5 3. Choked flow occurs when there is a flow restriction between two pressure regions. Assume an orifice and the pressure difference between the two sections, such as 2:1. Assume that the pressure in the inlet chamber is constant. The flow relation is, Q ~ P1 4. Molecular flow: When pressure reduces, MFP becomes larger than the dimensions of the duct, collisions occur between the walls of the vessel. -
Unit 11 Sound Speed of Sound Speed of Sound Sound Can Travel Through Any Kind of Matter, but Not Through a Vacuum
Unit 11 Sound Speed of Sound Speed of Sound Sound can travel through any kind of matter, but not through a vacuum. The speed of sound is different in different materials; in general, it is slowest in gases, faster in liquids, and fastest in solids. The speed depends somewhat on temperature, especially for gases. vair = 331.0 + 0.60T T is the temperature in degrees Celsius Example 1: Find the speed of a sound wave in air at a temperature of 20 degrees Celsius. v = 331 + (0.60) (20) v = 331 m/s + 12.0 m/s v = 343 m/s Using Wave Speed to Determine Distances At normal atmospheric pressure and a temperature of 20 degrees Celsius, speed of sound: v = 343m / s = 3.43102 m / s Speed of sound 750 mi/h Speed of light 670 616 629 mi/h c = 300,000,000m / s = 3.00 108 m / s Delay between the thunder and lightning Example 2: The thunder is heard 3 seconds after the lightning seen. Find the distance to storm location. The speed of sound is 345 m/s. distance = v t = (345m/s)(3s) = 1035m Example 3: Another phenomenon related to the perception of time delays between two events is an echo. In a canyon, an echo is heard 1.40 seconds after making the holler. Find the distance to the canyon wall (v=345m/s) distanceround trip = vt = (345 m/s )( 1.40 s) = 483 m d= 484/2=242m Applications: Sonar, Ultrasound, and Medical Imaging • Ultrasound or ultrasonography is a medical imaging technique that uses high frequency sound waves and their echoes. -
Atmospheric Cold Front-Generated Waves in the Coastal Louisiana
Journal of Marine Science and Engineering Article Atmospheric Cold Front-Generated Waves in the Coastal Louisiana Yuhan Cao 1 , Chunyan Li 2,* and Changming Dong 1,3,* 1 School of Marine Sciences, Nanjing University of Information Science and Technology, Nanjing 210044, China; [email protected] 2 Department of Oceanography and Coastal Sciences, College of the Coast and Environment, Louisiana State University, Baton Rouge, LA 70803, USA 3 Southern Laboratory of Ocean Science and Engineering (Zhuhai), Zhuhai 519000, China * Correspondence: [email protected] (C.L.); [email protected] (C.D.); Tel.: +1-225-578-2520 (C.L.); +86-025-58695733 (C.D.) Received: 15 October 2020; Accepted: 9 November 2020; Published: 11 November 2020 Abstract: Atmospheric cold front-generated waves play an important role in the air–sea interaction and coastal water and sediment transports. In-situ observations from two offshore stations are used to investigate variations of directional waves in the coastal Louisiana. Hourly time series of significant wave height and peak wave period are examined for data from 2004, except for the summer time between May and August, when cold fronts are infrequent and weak. The intra-seasonal scale variations in the wavefield are significantly affected by the atmospheric cold frontal events. The wave fields and directional wave spectra induced by four selected cold front passages over the coastal Louisiana are discussed. It is found that significant wave height generated by cold fronts coming from the west change more quickly than that by other passing cold fronts. The peak wave direction rotates clockwise during the cold front events. -
Mass Flow Rate and Isolation Characteristics of Injectors for Use with Self-Pressurizing Oxidizers in Hybrid Rockets
49th AIAA/ASME/SAE/ASEE Joint PropulsionConference AIAA 2013-3636 July 14 - 17, 2013, San Jose, CA Mass Flow Rate and Isolation Characteristics of Injectors for Use with Self-Pressurizing Oxidizers in Hybrid Rockets Benjamin S. Waxman*, Jonah E. Zimmerman†, Brian J. Cantwell‡ Stanford University, Stanford, CA 94305 and Gregory G. Zilliac§ NASA Ames Research Center, Moffet Field, CA 94035 Self-pressurizing rocket propellants are currently gaining popularity in the propulsion community, partic- ularly in hybrid rocket applications. Due to their high vapor pressure, these propellants can be driven out of a storage tank without the need for complicated pressurization systems or turbopumps, greatly minimizing the overall system complexity and mass. Nitrous oxide (N2O) is the most commonly used self pressurizing oxidizer in hybrid rockets because it has a vapor pressure of approximately 730 psi (5.03 MPa) at room temperature and is highly storable. However, it can be difficult to model the feed system with these propellants due to the presence of two-phase flow, especially in the injector. An experimental test apparatus was developed in order to study the performance of nitrous oxide injectors over a wide range of operating conditions. Mass flow rate characterization has been performed to determine the effects of injector geometry and propellant sub-cooling (pressurization). It has been shown that rounded and chamfered inlets provide nearly identical mass flow rate improvement in comparison to square edged orifices. A particular emphasis has been placed on identifying the critical flow regime, where the flow rate is independent of backpressure (similar to choking). For a simple orifice style injector, it has been demonstrated that critical flow occurs when the downstream pressure falls sufficiently below the vapor pressure, ensuring bulk vapor formation within the injector element. -
A Review of Ocean/Sea Subsurface Water Temperature Studies from Remote Sensing and Non-Remote Sensing Methods
water Review A Review of Ocean/Sea Subsurface Water Temperature Studies from Remote Sensing and Non-Remote Sensing Methods Elahe Akbari 1,2, Seyed Kazem Alavipanah 1,*, Mehrdad Jeihouni 1, Mohammad Hajeb 1,3, Dagmar Haase 4,5 and Sadroddin Alavipanah 4 1 Department of Remote Sensing and GIS, Faculty of Geography, University of Tehran, Tehran 1417853933, Iran; [email protected] (E.A.); [email protected] (M.J.); [email protected] (M.H.) 2 Department of Climatology and Geomorphology, Faculty of Geography and Environmental Sciences, Hakim Sabzevari University, Sabzevar 9617976487, Iran 3 Department of Remote Sensing and GIS, Shahid Beheshti University, Tehran 1983963113, Iran 4 Department of Geography, Humboldt University of Berlin, Unter den Linden 6, 10099 Berlin, Germany; [email protected] (D.H.); [email protected] (S.A.) 5 Department of Computational Landscape Ecology, Helmholtz Centre for Environmental Research UFZ, 04318 Leipzig, Germany * Correspondence: [email protected]; Tel.: +98-21-6111-3536 Received: 3 October 2017; Accepted: 16 November 2017; Published: 14 December 2017 Abstract: Oceans/Seas are important components of Earth that are affected by global warming and climate change. Recent studies have indicated that the deeper oceans are responsible for climate variability by changing the Earth’s ecosystem; therefore, assessing them has become more important. Remote sensing can provide sea surface data at high spatial/temporal resolution and with large spatial coverage, which allows for remarkable discoveries in the ocean sciences. The deep layers of the ocean/sea, however, cannot be directly detected by satellite remote sensors. -
Physics 101: Lecture 18 Fluids II
PhysicsPhysics 101:101: LectureLecture 1818 FluidsFluids IIII Today’s lecture will cover Textbook Chapter 9 Physics 101: Lecture 18, Pg 1 ReviewReview StaticStatic FluidsFluids Pressure is force exerted by molecules “bouncing” off container P = F/A Gravity affects pressure P = P 0 + ρgd Archimedes’ principle: Buoyant force is “weight” of displaced fluid. F = ρ g V Today include moving fluids! A1v1 = A 2 v2 – continuity equation 2 2 P1+ρgy 1 + ½ ρv1 = P 2+ρgy 2 + ½ρv2 – Bernoulli’s equation Physics 101: Lecture 18, Pg 2 08 ArchimedesArchimedes ’’ PrinciplePrinciple Buoyant Force (F B) weight of fluid displaced FB = ρfluid Vdisplaced g Fg = mg = ρobject Vobject g object sinks if ρobject > ρfluid object floats if ρobject < ρfluid If object floats… FB = F g Therefore: ρfluid g Vdispl. = ρobject g Vobject Therefore: Vdispl./ Vobject = ρobject / ρfluid Physics 101: Lecture 18, Pg 3 10 PreflightPreflight 11 Suppose you float a large ice-cube in a glass of water, and that after you place the ice in the glass the level of the water is at the very brim. When the ice melts, the level of the water in the glass will: 1. Go up, causing the water to spill out of the glass. 2. Go down. 3. Stay the same. Physics 101: Lecture 18, Pg 4 12 PreflightPreflight 22 Which weighs more: 1. A large bathtub filled to the brim with water. 2. A large bathtub filled to the brim with water with a battle-ship floating in it. 3. They will weigh the same. Tub of water + ship Tub of water Overflowed water Physics 101: Lecture 18, Pg 5 15 ContinuityContinuity A four-lane highway merges down to a two-lane highway. -
Physical Geography Chapter 5: Atmospheric Pressure, Winds, Circulation Patterns
Physical Geography Chapter 5: Atmospheric Pressure, Winds, Circulation Patterns Torricelli – 1643- first Mercury barometer (76 cm, 29.92 in) – measures response to pressure Pressure – millibars- 1013.2 mb, will cause Hg to rise in tube Unequal heating of Earth’s surface is responsible for differences in pressure to! Variations in Atmospheric Pressure 1. Vertical Variations – increase in elevation, less air pressure Mt. Everest – 8848 m (or 29, 028 ft) – 1/3 pressure 2. Horizontal Variations a. Thermal (determined by T) Warm air is less dense – it rises away from the surface at the equator b. Dynamic: Air from the tropics moves northward and then to the east due to the Coryolis Effect. It collects at this latitude, increasing pressure at the surface. Basic Pressure Systems 1. Low – cyclone – converging air pressure decreases 2. High – anticyclone – Divergins air pressure increases Wind Isobars- line of equal pressure Pressure Gradient - significant difference in pressure Wind- horizontal movement of air in response to differences in pressure ¾ Responsible for moving heat toward poles ¾ 38° Lat and lower: radiation surplus If Earth did not rotate, and if there wasno friction between moving air and the Earth’s surface, the air would flow in a straight line from areas of higher pressure to areas of low pressure. Of course, this is not true, the Earth rotates and friction exists: and wind is controlled by three major factors: 1) PGF- Pressure is measured by barometer 2) Coriolis Effect 3) Friction 1) Pressure Gradient Force (PGF) Pressure differences create wind, and the greater these differences, the greater the wind speed. -
Diving Air Compressor - Wikipedia, the Free Encyclopedia Diving Air Compressor from Wikipedia, the Free Encyclopedia
2/8/2014 Diving air compressor - Wikipedia, the free encyclopedia Diving air compressor From Wikipedia, the free encyclopedia A diving air compressor is a gas compressor that can provide breathing air directly to a surface-supplied diver, or fill diving cylinders with high-pressure air pure enough to be used as a breathing gas. A low pressure diving air compressor usually has a delivery pressure of up to 30 bar, which is regulated to suit the depth of the dive. A high pressure diving compressor has a delivery pressure which is usually over 150 bar, and is commonly between 200 and 300 bar. The pressure is limited by an overpressure valve which may be adjustable. A small stationary high pressure diving air compressor installation Contents 1 Machinery 2 Air purity 3 Pressure 4 Filling heat 5 The bank 6 Gas blending 7 References 8 External links A small scuba filling and blending station supplied by a compressor and Machinery storage bank Diving compressors are generally three- or four-stage-reciprocating air compressors that are lubricated with a high-grade mineral or synthetic compressor oil free of toxic additives (a few use ceramic-lined cylinders with O-rings, not piston rings, requiring no lubrication). Oil-lubricated compressors must only use lubricants specified by the compressor's manufacturer. Special filters are used to clean the air of any residual oil and water(see "Air purity"). Smaller compressors are often splash lubricated - the oil is splashed around in the crankcase by the impact of the crankshaft and connecting A low pressure breathing air rods - but larger compressors are likely to have a pressurized lubrication compressor used for surface supplied using an oil pump which supplies the oil to critical areas through pipes diving at the surface control point and passages in the castings. -
THERMODYNAMICS, HEAT TRANSFER, and FLUID FLOW, Module 3 Fluid Flow Blank Fluid Flow TABLE of CONTENTS
Department of Energy Fundamentals Handbook THERMODYNAMICS, HEAT TRANSFER, AND FLUID FLOW, Module 3 Fluid Flow blank Fluid Flow TABLE OF CONTENTS TABLE OF CONTENTS LIST OF FIGURES .................................................. iv LIST OF TABLES ................................................... v REFERENCES ..................................................... vi OBJECTIVES ..................................................... vii CONTINUITY EQUATION ............................................ 1 Introduction .................................................. 1 Properties of Fluids ............................................. 2 Buoyancy .................................................... 2 Compressibility ................................................ 3 Relationship Between Depth and Pressure ............................. 3 Pascal’s Law .................................................. 7 Control Volume ............................................... 8 Volumetric Flow Rate ........................................... 9 Mass Flow Rate ............................................... 9 Conservation of Mass ........................................... 10 Steady-State Flow ............................................. 10 Continuity Equation ............................................ 11 Summary ................................................... 16 LAMINAR AND TURBULENT FLOW ................................... 17 Flow Regimes ................................................ 17 Laminar Flow ............................................... -
Air Pressure and Wind
Air Pressure We know that standard atmospheric pressure is 14.7 pounds per square inch. We also know that air pressure decreases as we rise in the atmosphere. 1013.25 mb = 101.325 kPa = 29.92 inches Hg = 14.7 pounds per in 2 = 760 mm of Hg = 34 feet of water Air pressure can simply be measured with a barometer by measuring how the level of a liquid changes due to different weather conditions. In order that we don't have columns of liquid many feet tall, it is best to use a column of mercury, a dense liquid. The aneroid barometer measures air pressure without the use of liquid by using a partially evacuated chamber. This bellows-like chamber responds to air pressure so it can be used to measure atmospheric pressure. Air pressure records: 1084 mb in Siberia (1968) 870 mb in a Pacific Typhoon An Ideal Ga s behaves in such a way that the relationship between pressure (P), temperature (T), and volume (V) are well characterized. The equation that relates the three variables, the Ideal Gas Law , is PV = nRT with n being the number of moles of gas, and R being a constant. If we keep the mass of the gas constant, then we can simplify the equation to (PV)/T = constant. That means that: For a constant P, T increases, V increases. For a constant V, T increases, P increases. For a constant T, P increases, V decreases. Since air is a gas, it responds to changes in temperature, elevation, and latitude (owing to a non-spherical Earth). -
Aircraft Performance: Atmospheric Pressure
Aircraft Performance: Atmospheric Pressure FAA Handbook of Aeronautical Knowledge Chap 10 Atmosphere • Envelope surrounds earth • Air has mass, weight, indefinite shape • Atmosphere – 78% Nitrogen – 21% Oxygen – 1% other gases (argon, helium, etc) • Most oxygen < 35,000 ft Atmospheric Pressure • Factors in: – Weather – Aerodynamic Lift – Flight Instrument • Altimeter • Vertical Speed Indicator • Airspeed Indicator • Manifold Pressure Guage Pressure • Air has mass – Affected by gravity • Air has weight Force • Under Standard Atmospheric conditions – at Sea Level weight of atmosphere = 14.7 psi • As air become less dense: – Reduces engine power (engine takes in less air) – Reduces thrust (propeller is less efficient in thin air) – Reduces Lift (thin air exerts less force on the airfoils) International Standard Atmosphere (ISA) • Standard atmosphere at Sea level: – Temperature 59 degrees F (15 degrees C) – Pressure 29.92 in Hg (1013.2 mb) • Standard Temp Lapse Rate – -3.5 degrees F (or 2 degrees C) per 1000 ft altitude gain • Upto 36,000 ft (then constant) • Standard Pressure Lapse Rate – -1 in Hg per 1000 ft altitude gain Non-standard Conditions • Correction factors must be applied • Note: aircraft performance is compared and evaluated with respect to standard conditions • Note: instruments calibrated for standard conditions Pressure Altitude • Height above Standard Datum Plane (SDP) • If the Barometric Reference Setting on the Altimeter is set to 29.92 in Hg, then the altitude is defined by the ISA standard pressure readings (see Figure 10-2, pg 10-3) Density Altitude • Used for correlating aerodynamic performance • Density altitude = pressure altitude corrected for non-standard temperature • Density Altitude is vertical distance above sea- level (in standard conditions) at which a given density is to be found • Aircraft performance increases as Density of air increases (lower density altitude) • Aircraft performance decreases as Density of air decreases (higher density altitude) Density Altitude 1.