Jet Propulsion and the Evolution of the Cephalopods

Total Page:16

File Type:pdf, Size:1020Kb

Jet Propulsion and the Evolution of the Cephalopods BULLETIN OF MARINE SCIENCE, 49(1-2): 419-432, 1991 JET PROPULSION AND THE EVOLUTION OF THE CEPHALOPODS M. J. Wells and R. K. O'Dor ABSTRACT The first cephalopods, recognized as such by their possession of a chambered shell with a siphuncle, appeared in the late Cambrian. They are assumed to have been crawling animals. Lightening the shell, made possible by ion and water removal and the consequent appearance of gas in the chambers would have allowed the animal to escape upwards, using the jet resulting from a sudden withdrawal of the body into the shell. Nautilus still produces a propulsive jet in this manner. It can also generate a low pressure stream using the wings of the funnel to waft a flow through the gills. It is argued that all the other ectocochleates would have had propulsive mechanisms based on one or other (or both) of the means by which Nautilus develops ajet. One consequence of this conclusion is that none of them were powerful swimmers. The momentum imparted by a jet depends upon the ejected mass multiplied by the velocity of the jet. But E = lhmv' so that while slow speed propulsion using the ventilation stream can result in a very low cost of transport any attempt to achieve high speeds is very costly. Only marginal improvements could be made by lightening or streamlining the shell. More economical fast locomotion could only be achieved by increasing the volume of the mantle cavity, and this meant scrapping or internalizing the shell. It also necessitated the development ofa new set of propulsive muscles, in the wall of the mantle. Mantle musculature now took on both locomotor and ventilatory functions. The two functions have incompatible requirements; for efficient jet propulsion the stream volume should be maximized, while efficient oxygen uptake should minimize the flow. Octopods have optimized oxygen extrac- tion, the squids, in general are specialized for jet propulsion. In the teuthoids and octopods progressive shell reduction also led to the loss of neutral buoyancy, regained in some forms by ion-substitution in the tissues and an associated return to relatively slow-moving lifestyles. Jet propulsion remained an extravagant form of propulsion at all but the slowest speeds. Many coleoids, as a result, have moved on to develop yet another locomotor system, replacing jet propulsion by undulant fins. The one fact that everybody seems to know about cephalopods is that they are jet-propelled. What is less universally recognized is that many have additional means of moving, swimming by the use of fins or crawling on their arms, so that jet propulsion often constitutes a secondary rather than their primary means of locomotion. It is also often forgotten that the early shelled cephalopods used two quite different means of generating the jet, neither of which is found in the modern coleoids. This paper is a brief survey of the likely history ofjet propulsion in cephalopods, concentrating particularly on the state of affairs in the many forms with external shells, now almost universally extinct. From what we now know of the living Nautilus, it is possible to reconstruct the likely swimming performance of am- monoids and nautiloids, and to understand why the shelled forms were progres- sively replaced as sea conditions changed to favor the faster-moving coleoids. The Earliest Cephalopods. - The earliest mollusc unequivocally recognizable as a cephalopod is the late Cambrian Plectronoceras. The animal, believed to be de- rived from tall, endogastric monoplacophores, had septa and a siphuncle (Yoch- elson et al., 1973; Webers and Yochelson, 1989). The chambers could have been fluid or gas filled; the body in the final chamber was attached by muscles that would have pulled an assumed head and foot back into safety when danger threat- ened. Since the animal was largely enclosed in a shell, it must have had gills to 419 420 BULLETIN OF MARINE SCIENCE, VOL. 49, NO. 1-2,1991 increase the respiratory area and a pumped circulatory system. Gills are, in their nature, vulnerable, so it is reasonable to assume that Plectronoceras also had a mantle cavity. A sudden withdrawal of the head and body into the protection of the shell (the traditional medieval defense of molluscs) would have displaced fluid from the mantle cavity. This, one must suppose, was the origin of the jet; Nautilus. as we shall see, still produces a jet in this manner. The sudden backward thrust would itself have constituted a means of escape and any lightening of the shell would have improved the performance (dilution and gas production are linked, since withdrawal of salts sets up an osmotic gradient; water follows, dropping the pres- sure in the chambe:rs, causing gas to come out of solution in the blood-Denton and Gilpin-Brown, 1966). Neutral buoyancy, a further development of the ten- dency to lighten the: shell, freed the foot from its locomotor functions and allowed it, on the one hand, to extend as flaps that could be overlapped to form a jet- directing funnel, and, together with the head, to extend as a series of grasping tentacles. The early cephalopods presumably had beaks and a radula, since all their descendants did SO; they could have been scavengers, but they were also well suited to a predatory existence, dropping from above on the bottom-living fauna below. Straight Nautiloids. - The resulting animals did well, and the rapid evolution of a whole range of curved and straight nautiloids, some of massive size, was un- stoppable (Teichert, 1967). For a long time these animals dominated the marine mid-water (or, perhaps more accurately nekto-benthic) environment, cruising at will above the seafloor where their prey and potential competitors were still in the main defeated by gravity. Sharks did not appear until the Devonian, almost 100 million years later. A long straight or slightly coiled shell is a difficult thing to maneuver, even given a funnel capable of directing the jet. It cannot readily be propelled backwards, because it will slew to one side; a rocket can correct for this, but it is difficult to envisage an effective system based on a pulsed jet. The alternative of spinning the shell along its longitudinal axis is plainly absurd. The limited evidence that we have suggests that all but the earliest, ellesmer- oceratid, straight nautiloids moved with their shells horizontal. The first formed chambers typically show additional mineral deposits, assumed to be counter- weights laid down as the animal grew. Because of the difficulty of steering, straight nautiloids probably swam head first, with the jet directed backwards, under the animal, as Nautilus can do today (Fig. I). Tracks in Ordovician rocks terminating in orthocone shells (Orthonybyoceras) show that animals grounding to die came in blunt end first (Flower, 1955; other trace fossils, interpreted as tentacle marks in the same work are now believed to be worm tubes, see Osgood, 1970) Jet Propulsion in Nautilus. -Coiled nautiloids appeared in the early Ordovician. This modification of the design has a number of advantages. It keeps the center of buoyancy above the center of gravity, so there is no need to weight the apex of the shell. Even the modem, coiled Nautilus uses something like 80% of its buoyancy to support the shell (Denton and Gilpin-Brown, 1966), and any further addition of weight reduces the buoyancy available to support body flesh. Coiling, moreover, economizes in shell materials, since each whorl builds on the one before and mineral ballasting is unnecessary. And it makes the animal much more ma- neuverable, both forwards and backwards. The six living species of Nautilus all conform to this pattern. They are totally dependent upon the jet for propulsion. Since the shell form so closely resembles that of some Palaeozoic ectocochleates, WELLS AND O'DOR: EVOLUTION OF JET PROPULSION 421 Head RETRACTOR MUSCLE ATTACHMENT Figure I, Two means of producing a jet in Nautilus: 1) The very large paired head retractor muscles can pull down the head, expelling all water from the mantle cavity. 2) The wings of the funnel folds, hanging down from above and overlapping below, contract rhythmically to waft a steady flow of water (arrows) down through the gills and out through the funnel. The contents of the mantle cavity are shown a) from the right side and b) from below, Inset c) shows how the very flexible funnel can move to direct the jet to the side or backwards. (c) After Packard et al. (1980), it seems reasonable to conclude that Nautilus develops the jet in the same manner as did its ancestors. In fact, it generates the jet in two distinct ways. One of these reflects the ancestral escape mechanism; the head is drawn down into the shell aperture by the massive head retractor muscles, displacing water from the mantle cavity. The funnel is formed from two folds of muscle, hanging down from either side of the head, overlapping to form a highly maneuverable spout (Fig. 1). From the roof of the funnel hangs a flap-valve, so that water is not readily drawn back in by this route. Instead, re-extension of the head, caused by the active contraction of radial fibers in the head retractor muscles, plus, no doubt, by some elasticity in the rubbery head shield, sucks in water close to the umbilicus on either side; rearward exten- sions of the funnel folds here form further one-way valves. The second jet-producing system is the funnel itself. The very large funnel folds extend back along the whole length of the mantle cavity on either side. In quiet ventilation, these "wings" of the funnel perform an elaborate peristaltic move- 422 BULLETIN OF MARINE SCIENCE, VOL.
Recommended publications
  • Propulsion Systems for Aircraft. Aerospace Education II
    . DOCUMENT RESUME ED 111 621 SE 017 458 AUTHOR Mackin, T. E. TITLE Propulsion Systems for Aircraft. Aerospace Education II. INSTITUTION 'Air Univ., Maxwell AFB, Ala. Junior Reserve Office Training Corps.- PUB.DATE 73 NOTE 136p.; Colored drawings may not reproduce clearly. For the accompanying Instructor Handbook, see SE 017 459. This is a revised text for ED 068 292 EDRS PRICE, -MF-$0.76 HC.I$6.97 Plus' Postage DESCRIPTORS *Aerospace 'Education; *Aerospace Technology;'Aviation technology; Energy; *Engines; *Instructional-. Materials; *Physical. Sciences; Science Education: Secondary Education; Textbooks IDENTIFIERS *Air Force Junior ROTC ABSTRACT This is a revised text used for the Air Force ROTC _:_progralit._The main part of the book centers on the discussion -of the . engines in an airplane. After describing the terms and concepts of power, jets, and4rockets, the author describes reciprocating engines. The description of diesel engines helps to explain why theseare not used in airplanes. The discussion of the carburetor is followed byan explanation of the lubrication system. The chapter on reaction engines describes the operation of,jets, with examples of different types of jet engines.(PS) . 4,,!It********************************************************************* * Documents acquired by, ERIC include many informal unpublished * materials not available from other souxces. ERIC makes every effort * * to obtain the best copravailable. nevertheless, items of marginal * * reproducibility are often encountered and this affects the quality * * of the microfiche and hardcopy reproductions ERIC makes available * * via the ERIC Document" Reproduction Service (EDRS). EDRS is not * responsible for the quality of the original document. Reproductions * * supplied by EDRS are the best that can be made from the original.
    [Show full text]
  • Comparison of Helicopter Turboshaft Engines
    Comparison of Helicopter Turboshaft Engines John Schenderlein1, and Tyler Clayton2 University of Colorado, Boulder, CO, 80304 Although they garnish less attention than their flashy jet cousins, turboshaft engines hold a specialized niche in the aviation industry. Built to be compact, efficient, and powerful, turboshafts have made modern helicopters and the feats they accomplish possible. First implemented in the 1950s, turboshaft geometry has gone largely unchanged, but advances in materials and axial flow technology have continued to drive higher power and efficiency from today's turboshafts. Similarly to the turbojet and fan industry, there are only a handful of big players in the market. The usual suspects - Pratt & Whitney, General Electric, and Rolls-Royce - have taken over most of the industry, but lesser known companies like Lycoming and Turbomeca still hold a footing in the Turboshaft world. Nomenclature shp = Shaft Horsepower SFC = Specific Fuel Consumption FPT = Free Power Turbine HPT = High Power Turbine Introduction & Background Turboshaft engines are very similar to a turboprop engine; in fact many turboshaft engines were created by modifying existing turboprop engines to fit the needs of the rotorcraft they propel. The most common use of turboshaft engines is in scenarios where high power and reliability are required within a small envelope of requirements for size and weight. Most helicopter, marine, and auxiliary power units applications take advantage of turboshaft configurations. In fact, the turboshaft plays a workhorse role in the aviation industry as much as it is does for industrial power generation. While conventional turbine jet propulsion is achieved through thrust generated by a hot and fast exhaust stream, turboshaft engines creates shaft power that drives one or more rotors on the vehicle.
    [Show full text]
  • 2. Afterburners
    2. AFTERBURNERS 2.1 Introduction The simple gas turbine cycle can be designed to have good performance characteristics at a particular operating or design point. However, a particu­ lar engine does not have the capability of producing a good performance for large ranges of thrust, an inflexibility that can lead to problems when the flight program for a particular vehicle is considered. For example, many airplanes require a larger thrust during takeoff and acceleration than they do at a cruise condition. Thus, if the engine is sized for takeoff and has its design point at this condition, the engine will be too large at cruise. The vehicle performance will be penalized at cruise for the poor off-design point operation of the engine components and for the larger weight of the engine. Similar problems arise when supersonic cruise vehicles are considered. The afterburning gas turbine cycle was an early attempt to avoid some of these problems. Afterburners or augmentation devices were first added to aircraft gas turbine engines to increase their thrust during takeoff or brief periods of acceleration and supersonic flight. The devices make use of the fact that, in a gas turbine engine, the maximum gas temperature at the turbine inlet is limited by structural considerations to values less than half the adiabatic flame temperature at the stoichiometric fuel-air ratio. As a result, the gas leaving the turbine contains most of its original concentration of oxygen. This oxygen can be burned with additional fuel in a secondary combustion chamber located downstream of the turbine where temperature constraints are relaxed.
    [Show full text]
  • Novel Distributed Air-Breathing Plasma Jet Propulsion Concept for All-Electric High-Altitude Flying Wings
    Novel Distributed Air-Breathing Plasma Jet Propulsion Concept for All-Electric High-Altitude Flying Wings B. Goeksel1 IB Goeksel Electrofluidsystems, Berlin, Germany, 13355 The paper describes a novel distributed air-breathing plasma jet propulsion concept for all-electric hybrid flying wings capable of reaching altitudes of 100,000 ft and subsonic speeds of 500 mph, Fig. 1. The new concept is based on the recently achieved first breakthrough for air-breathing high-thrust plasma jet engines.5 Pulse operation with a few hundred Hertz will soon enable thrust levels of up to 5-10 N from each of the small trailing edge plasma thruster cells with one inch of core engine diameter and thrust-to-area ratios of modern fuel-powered jet engines. An array of tens of thrusters with a magnetohydrodynamic (MHD) fast jet core and low speed electrohydrodynamic (EHD) fan engine based on sliding discharges on new ultra-lightweight structures will serve as a distributed plasma “rocket” booster for a short duration fast climb from 50,000 ft to stratospheric altitudes up to 100,000 ft, Fig. 2. Two electric aircraft engines with each 110 lb (50 kg) weight and 260 kW of power as recently developed by Siemens will make the main propulsion for take-off and landing and climb up to 50,000 ft.3 4 Especially for climbing up to 100,000 ft the propellers will apply sophisticated pulsed plasma separation flow control methods. The novel distributed air-breathing plasma engine will be only powered for a short duration to reach stratospheric altitudes with lowest possible power consumption from the high-density battery swap modules and special fuel cell systems with minimum 660 kW, all system optimized for a short one to two hours near- space tourism flight application.2 The shining Plasma Stingray shown in Fig.
    [Show full text]
  • New Dawn for Electric Rockets
    SPACE TECHNOLOGY New Dawn for KEY CONCEPTS Ef!cient electric plasma engines are ■ Conventional rockets propelling the next generation of space generate thrust by burning chemical fuel. Electric probes to the outer solar system By Edgar Y. Choueiri rockets propel space vehicles by applying electric or electromagnetic !elds to clouds of charged lone amid the cosmic blackness, NASA’s ing liquid or solid chemical fuels, as convention- particles, or plasmas, to Dawn space probe speeds beyond the al rockets do. accelerate them. A orbit of Mars toward the asteroid belt. Dawn’s mission designers at the NASA Jet Launched to search for insights into the birth of Propulsion Laboratory selected a plasma engine ■ Although electric rockets the solar system, the robotic spacecraft is on its as the probe’s rocket system because it is highly offer much lower thrust levels than their chemical way to study the asteroids Vesta and Ceres, two ef"cient, requiring only one tenth of the fuel cousins, they can even- of the largest remnants of the planetary embry- that a chemical rocket motor would have need- tually enable spacecraft os that collided and combined some 4.57 billion ed to reach the asteroid belt. If project planners to reach greater speeds years ago to form today’s planets. had chosen to install a traditional engine, the for the same amount But the goals of the mission are not all that vehicle would have been able to reach either of propellant. make this !ight notable. Dawn, which took off Vesta or Ceres, but not both. ■ Electric rockets’ high-speed in September 2007, is powered by a kind of space Indeed, electric rockets, as the engines are also capabilities and their propulsion technology that is starting to take known, are quickly becoming the best option for ef!cient use of propellant center stage for long-distance missions—a plas- sending probes to far-off targets.
    [Show full text]
  • Introduction to Turboprop Engine Types
    INTRODUCTION TO TURBOPROP ENGINE TYPES The turbopropeller engine consists of a gas turbine engine driving a propeller. Most of the energy of the gas flow (air and burned fuel) is used to drive the propeller and compressor. The remaining energy, in the form of differential velocity of the airflow exiting the turbine, provides a small amount of residual thrust (effectively, a small amount of jet propulsion). Additional information on the specifics of the gas turbine cycle is provided elsewhere in this training package. There are two basic types of turboprop engines: 1. Single shaft 2. Free turbine The main difference between single shaft and free turbines is in the transmission of the power to the propeller. In the majority of turboprops, the fuel pump is driven by the engine. This is known as "direct drive.” In some older types of engines, the fuel pump is driven by the propeller, which can affect proper response to an engine failure. Refer to type-specific procedures. Single Shaft. In a single-shaft engine, the propeller is driven by the same shaft (spool) that drives the compressor. Because the propeller needs to rotate at a lower RPM than the turbine, a reduction gearbox reduces the engine shaft rotational speed to accommodate the propeller through the propeller drive shaft. Free Turbine. In a free-turbine engine, the propeller is driven by a dedicated turbine. A different turbine drives the compressor; this turbine and its compressor run at near-constant RPM regardless of the propeller pitch and speed. Because the propeller needs to rotate at lower RPM than the turbine, a reduction gearbox converts the turbine RPM to an appropriate level for the propeller.
    [Show full text]
  • Space Propulsion Technology for Small Spacecraft
    Space Propulsion Technology for Small Spacecraft The MIT Faculty has made this article openly available. Please share how this access benefits you. Your story matters. Citation Krejci, David, and Paulo Lozano. “Space Propulsion Technology for Small Spacecraft.” Proceedings of the IEEE, vol. 106, no. 3, Mar. 2018, pp. 362–78. As Published http://dx.doi.org/10.1109/JPROC.2017.2778747 Publisher Institute of Electrical and Electronics Engineers (IEEE) Version Author's final manuscript Citable link http://hdl.handle.net/1721.1/114401 Terms of Use Creative Commons Attribution-Noncommercial-Share Alike Detailed Terms http://creativecommons.org/licenses/by-nc-sa/4.0/ PROCC. OF THE IEEE, VOL. 106, NO. 3, MARCH 2018 362 Space Propulsion Technology for Small Spacecraft David Krejci and Paulo Lozano Abstract—As small satellites become more popular and capa- While designations for different satellite classes have been ble, strategies to provide in-space propulsion increase in impor- somehow ambiguous, a system mass based characterization tance. Applications range from orbital changes and maintenance, approach will be used in this work, in which the term ’Small attitude control and desaturation of reaction wheels to drag com- satellites’ will refer to satellites with total masses below pensation and de-orbit at spacecraft end-of-life. Space propulsion 500kg, with ’Nanosatellites’ for systems ranging from 1- can be enabled by chemical or electric means, each having 10kg, ’Picosatellites’ with masses between 0.1-1kg and ’Fem- different performance and scalability properties. The purpose tosatellites’ for spacecrafts below 0.1kg. In this category, the of this review is to describe the working principles of space popular Cubesat standard [13] will therefore be characterized propulsion technologies proposed so far for small spacecraft.
    [Show full text]
  • Jet Propulsion Engines
    JET PROPULSION ENGINES 5.1 Introduction Jet propulsion, similar to all means of propulsion, is based on Newton’s Second and Third laws of motion. The jet propulsion engine is used for the propulsion of aircraft, m issile and submarine (for vehicles operating entirely in a fluid) by the reaction of jet of gases which are discharged rearw ard (behind) with a high velocity. A s applied to vehicles operating entirely in a fluid, a momentum is imparted to a mass of fluid in such a manner that the reaction of the imparted momentum furnishes a propulsive force. The magnitude of this propulsive force is termed as thrust. For efficient production of large power, fuel is burnt in an atmosphere of compressed air (combustion chamber), the products of combustion expanding first in a gas turbine which drives the air compressor and then in a nozzle from which the thrust is derived. Paraffin is usually adopted as the fuel because of its ease of atomisation and its low freezing point. Jet propulsion was utilized in the flying Bomb, the initial compression of the air being due to a divergent inlet duct in which a sm all increase in pressure energy w as obtained at the expense of kinetic energy of the air. Because of this very limited compression, the thermal efficiency of the unit was low, although huge power was obtained. In the normal type of jet propulsion unit a considerable improvement in efficiency is obtained by fitting a turbo-com pressor which w ill give a com pression ratio of at least 4:1.
    [Show full text]
  • Aircraft Propulsion C Fayette Taylor
    SMITHSONIAN ANNALS OF FLIGHT AIRCRAFT PROPULSION C FAYETTE TAYLOR %L~^» ^ 0 *.». "itfnm^t.P *7 "•SI if' 9 #s$j?M | _•*• *• r " 12 H' .—• K- ZZZT "^ '! « 1 OOKfc —•II • • ~ Ifrfil K. • ««• ••arTT ' ,^IfimmP\ IS T A Review of the Evolution of Aircraft Piston Engines Volume 1, Number 4 (End of Volume) NATIONAL AIR AND SPACE MUSEUM 0/\ SMITHSONIAN INSTITUTION SMITHSONIAN INSTITUTION NATIONAL AIR AND SPACE MUSEUM SMITHSONIAN ANNALS OF FLIGHT VOLUME 1 . NUMBER 4 . (END OF VOLUME) AIRCRAFT PROPULSION A Review of the Evolution 0£ Aircraft Piston Engines C. FAYETTE TAYLOR Professor of Automotive Engineering Emeritus Massachusetts Institute of Technology SMITHSONIAN INSTITUTION PRESS CITY OF WASHINGTON • 1971 Smithsonian Annals of Flight Numbers 1-4 constitute volume one of Smithsonian Annals of Flight. Subsequent numbers will not bear a volume designation, which has been dropped. The following earlier numbers of Smithsonian Annals of Flight are available from the Superintendent of Documents as indicated below: 1. The First Nonstop Coast-to-Coast Flight and the Historic T-2 Airplane, by Louis S. Casey, 1964. 90 pages, 43 figures, appendix, bibliography. Price 60ff. 2. The First Airplane Diesel Engine: Packard Model DR-980 of 1928, by Robert B. Meyer. 1964. 48 pages, 37 figures, appendix, bibliography. Price 60^. 3. The Liberty Engine 1918-1942, by Philip S. Dickey. 1968. 110 pages, 20 figures, appendix, bibliography. Price 75jf. The following numbers are in press: 5. The Wright Brothers Engines and Their Design, by Leonard S. Hobbs. 6. Langley's Aero Engine of 1903, by Robert B. Meyer. 7. The Curtiss D-12 Aero Engine, by Hugo Byttebier.
    [Show full text]
  • FUEL SYSTEMS TECHNOLOGY OVERVIEW Rob E R T F Riedma N National Aeronautics and Space Administration Lewis Research Center Fuel S
    FUEL SYSTEMS TECHNOLOGY OVERVIEW Rob e r t F riedma n National Aeronautics and Space Administration Lewis Research Center Fuel system research and technology studies are being conducted to in- vestigate the correlations and interactions of aircraft fuel system design and environment with applicable characteristics of the fuel. Fuel Properties and the Fuel System Voluntary industry standards for aviation turbine fuel (ASTM D 1655, ref. 1) include over 25 items of specification, but only a few of these are of concern to the fuel system design and operation. The proceedings of a 1977 NASA-sponsored workshop on fuels (ref. 2) identified several fuel prop- erties worthy of further research with respect to their influence on the performance of present and future aircraft fuel systems. These properties include water solubility, viscosity, flashpoint, aromatics content, and freezing point. Water solubility is a minor characteristic, but it is a property sensitive to fuel composition; and changes in the fuel chemical constituents may increase the solubility and cause cleanliness problems. Viscosity is of concern with respect to lowtemperature pumpability, but praposed research on viscosity can be included with the freezing-point stu- dies discussed later. Flashpoint was not included among the cited proper ties in the reference 2 workshop proceedings. The workshop participants discussed flashpoint but concluded that safety and altitude boiloff limits made any changes or research on flashpoint unlikely. Subsequent to this workshop, an ASTM symposium reviewed the question of jet fuel flashpoint, its measurement, and the advantages and disadvantages of changes in the flashpoint specification. A compilation of the f lashpoint symposium papers has been recently published ( ref.
    [Show full text]
  • Jet Propulsion Test Stand P371
    P.A. Hilton Ltd Jet Propulsion Test Stand P371 Demonstration and thermodynamic investigation of the simplest form of heat engine. Low cost, aircraft propulsion system investigation. Negligible operating cost and no moving parts requiring maintenance Two year warranty Page 1 Edition 2 P.A. Hilton Ltd Introduction Ram Jet Engine The ramjet, the simplest concept of aircraft For operation the ramjet requires incoming air propulsion, consists of an almost cylindrical to have a significant approach velocity in order duct, open at both ends. It relies on its forward to maintain combustion. The forward speed is speed to ram air into the forward opening. Fuel simulated by a single stage blower delivering is burnt inside the duct to accelerate the air air through a 76mm diameter nozzle mounted stream, which together with the products of 200mm in front of the air intake. The use of combustion, issues from the rear as a high gaseous fuel makes a low operating speed and velocity jet. The change in momentum in the therefore a moderate air supply requirement engine provides the propulsive force. well within the reach of any engineering Also supplied is a pulsejet engine, which laboratory. utilises a cyclic combustion process but is unique in design in that like the ramjet, it has no moving parts. The Hilton P371 Jet Propulsion Test Stand will provide interesting and instructive experimental activity for all students studying thermodynamics and propulsion and will be of particular interest to those studying: • Thermodynamics The ramjet engine is fabricated from a heat • Heat Transfer resistant alloy and requires no maintenance • Aeronautical engineering even after many years of operation.
    [Show full text]
  • Aviation Fuels Technical Review
    Aviation Fuels Technical Review | Chevron Products Aviation Fuels Company Technical Review Chevron Products Company 6001 Bollinger Canyon Road San Ramon, CA 94583 Chevron Products Company is a division of a wholly owned subsidiary of Chevron Corporation. http://www.chevron.com/productsservices/aviation/ © 2007 Chevron U.S.A. Inc. All rights reserved. Chevron and the Caltex, Chevron and Texaco hallmarks are federally registered trademarks of Chevron Intellectual Property LLC. Recycled/RecyclableRecycled/recyclable paper paper IDC 1114-099612 MS-9891 (11/14) Table of Contents Notes General Introduction ............................................................i 8 • Aviation Gasoline Performance ............................ 45 Performance Properties 1 • Aviation Turbine Fuel Introduction ........................... 1 Cleanliness Types of Fuel Safety Properties Fuel Consumption 9 • Aviation Gasoline 2 • Aviation Turbine Fuel Performance .........................3 Specifications and Test Methods .......................... 54 Performance Properties Specifications Cleanliness Future Fuels Safety Properties Test Methods Emissions 10 • Aviation Gasoline Composition ............................. 63 3 • Aviation Turbine Fuel Composition Specifications and Test Method ...............................14 Property/Composition Relationships Specifications Additives Test Methods 11 • Aviation Gasoline Refining ..................................... 66 4 • Aviation Turbine Fuel Composition ........................24 Alkylation Base Fuel Avgas Blending
    [Show full text]