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Return of Supersonic Air Travel?

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楼主
发表于 12-26-2018 15:39:30 | 只看该作者 回帖奖励 |倒序浏览 |阅读模式
本帖最后由 choi 于 12-26-2018 17:02 编辑

This article is interesting. But if you are not into aerospace, you need not read the entire article; the quotations are enough.


Aerospace | Second Time Lucky?  A new engine could herald the return of supersonic air travel. Economist, Dec 15, 2018/
https://www.economist.com/scienc ... personic-air-travel

Quote:

(a) "Supersonic passenger travel came to an end in 2003. The crash three years earlier of a French Concorde had not helped, but the main reasons were wider. One was the aircraft’s Rolls-Royce/Snecma Olympus engines, afterburners and all, which gobbled up too much fuel for its flights to be paying propositions. The second was the boom-causing shock wave it generated when travelling supersonically. That meant the overland sections of its route had to be flown below Mach 1. For the Olympus, an engine optimised for travel far beyond the sound barrier, this was commercial death.  That, however, was then. And this is now. Materials are lighter and stronger. Aerodynamics and the physics of sonic booms are better understood.

(b) "General Electric (GE) * * * has teamed up with one of the groups of engineers , at Aerion, a company based in Reno, Nevada, to design an engine called affinity * * * [whose] prototypes have [not] been built and tested [and which aims for a top speed of Mach 1.4,] slower than Concord, which could belt along at just over Mach 2.

(c) "Force majeure [(which is sectional heading):] Like all jet engines, Affinity relies for its propulsion on Newton's third law of motion (to every action there is an equal and opposite reaction). The action comes from the mass of air drawn into the engine's front opening being thrust out of the back at far greater velocity. The reaction against thia action propels the engine, and anything attached to it, in the opposite direction -- ie, forward.

"In a simple jet the injected air is first squeezed by a compressor, and then mixed with fuel and ignited in the engine's core to create a fast-moving exhaust. Modern fan jets, however, use some of the exhaust energy to drive a shaft which turns a fan near the engine's intake. That fan pushes a proportion of the incoming air, known as the 'bypass,' around the engine's hot core and out of the back, thus providing additional thrust. Bypass thrust os more economical to create than core thrust, but it i slower moving. A supersonic aircraft can therefore afford only a small bypass ratio (1:1 in the case of many military jets). In a civil airliner the bypass ratio (which, if high, brings not only efficiency but also quietude) may be as great as 10:1.

"Affinity is a compromise between the two approaches, combining technologies from military and civil engines, Though its designers have not revealed its actual ratio(and much else, too, is secret at the moment), they describe it as a 'medium bypass' engine, and have said that it has a bigger fan than any other supersonic engine. Nor does it require an afterburner.

(d) "A particular design challenge, observes Brad Mottier, one of the GE executives leading the project, was that unlike conventional civil jet engines, which hang from an aircraft's wings, Affinity has to blend into a plane's airframe. The law of aerodynamics requires this if it is to perform efficiently. Blending also helps damp down the generation of a sonic boom. Sonic booms are caused by air piling up in front of various parts of the plane, particularly its nose, wings and engine inlets. This air turns into a shock wave that contains a huge amount of energy, which offends the ears when it reaches the ground. Blending engine and body, together design tweaks such as a specially shaped long, thin nose, can muffle a sonic boom befre it gets going.  To mute it [sonic boom] after it has happened [there are ways] * * *

My comment:
(a)
(i) I am not interested in sonic boom.
(ii) The discussion will focus on jet engines only, especially how they work.
(iii) More than a decade ago at Mitbbs.com, I had posting about jet engines, who tried his best to comprehend them. One asked what made fan blowing backward rather than forward. It was easy to answer: just like the house fan, whose shape and curvature determine airflow direction. Another asked: in a turbofan, which contributed to engine performance -- was it bypass or hot air created by burned fuel?  Now I can answer "both."
(iv) Upon reading the quotations in the Economist, I was awed. Further study shows they (quotations) are ordinary stuff, which, however, will serve as inspiration to understand jet engines.

(b)
(i) turbine (n; First Known Use  mid 19th century; from French [noun of the same spelling], from Latin [noun masculine] turbō, turbin-  spinning top, whirl [as in tornado, whirlwind]):
"a machine for producing continuous power in which a wheel or rotor, typically fitted with vanes, is made to revolve by a fast-moving flow of water, steam, gas, air, or other fluid"
https://en.oxforddictionaries.com/definition/turbine
(ii) en.wikipedia.org for turbine: section 1 Operational theory: "A working fluid contains potential energy [位能 in Taiwan] (pressure head) and kinetic energy (velocity head)."
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沙发
 楼主| 发表于 12-26-2018 15:43:28 | 只看该作者
(c)
(i) force majeure (n; First Known Use 1883; Did You Know?)
https://www.merriam-webster.com/dictionary/majeure
(ii) French-English dictionary:
* force (noun feminine; from Latin [noun feminine] fortia [force, strength], from Latin [adjective masculine/feminine] fortis strong): "force"
https://en.wiktionary.org/wiki/force

The English noun force is a direct descendant of the French noun feminine force.
* majeur (adj; from Latin [adjective] māior larger, greater; feminine singular  majeure): "greater, larger, more important"
https://en.wiktionary.org/wiki/majeur#French

The (irregular) comparative and superlative of Latin adjective masculine magnus is maior (later major) and maximus, respectively.

Latin alphabet
https://en.wikipedia.org/wiki/Latin_alphabet
(section 1 History, section 1.2 Medieval and later developments: letters w, j and v)

(d)
(i) Turbojet, turbofan and turboprop ALL have a fan at the engine inlet to draw in the air (to feed the engine/turbine at least, if not bypass also -- but turbojet has no bypass. See (f)(i)).
(ii) In a spectrum from turbojet at one end, through turbofan (low bypass ratio) and turbofan (high bypass ratio), to turboprop (to a certain extent regarding energy efficient) at the other end, both noise and energy efficiency increase. For the energy efficient only (but not noise, that is), see

bypass ratio
https://en.wikipedia.org/wiki/Bypass_ratio
(figure caption: "Propulsive efficiency comparison for various gas turbine engine configurations")
There is no need to read the rest of this Wiki page.

This is because fan diameter increases from turbojet toward turboprop.
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板凳
 楼主| 发表于 12-26-2018 15:44:23 | 只看该作者
(e)
(i) a general principle:

Why Are Turbofans More Efficient Than Turbojets?
https://www.quora.com/Why-are-tu ... ient-than-turbojets
(Kim Aaron answered on June 11, 2017: "The [turbo]jet engine is simpler and cheaper and smaller for the same thrust. But it uses more fuel othan turbofan]")

A 1985 PhD in aeronautics from California Institute of Technology (CalTech), Aaron is "one of three Chief Engineers in the Payload and Small Spacecraft Mechanical Engineering Section at Jet Propulsion Laboratory (JPL), CalYech."  per his own LinkedIn page.

kinetic energy
https://en.wikipedia.org/wiki/Kinetic_energy
(section 3 Newtonian kinetic energy, section 3.1 Kinetic energy of rigid bodies: equation)
(ii) Thrust moves the engine/turbine, hence the airplane.

"Thrust is a reaction force described quantitatively by Newton's third law. * * * Force, and thus thrust, is measured using the International System of Units (SI) in newtons (symbol: N), and represents the amount needed to accelerate 1 kilogram of mass at the rate of 1 meter per second per second."
https://en.wikipedia.org/wiki/Thrust

Pay attention to "reaction" in sentence 1.

Newton's second law of motion: F=ma, where m is mass and a, acceleration.
(iii)
(A) momentum
https://en.wikipedia.org/wiki/Momentum
(p=mv; section 1.3 Relation to force: F=dp/dt)
(B)  Why Is P the Symbol for Momentum?
https://www.quora.com/Why-is-P-the-symbol-for-momentum
("riya JL, Foodie!!!!
Answered Apr 9, 2015
It is because m was already taken for mass, for that matter all the other letters were taken.  p is used because the word impetus [the nouns spelled the same in both English and Latin] formally in place of momentum comes from the latin [verb], petere [seek], hence we get p")

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4#
 楼主| 发表于 12-26-2018 15:45:51 | 只看该作者
(f) thrust equations:
(i) turbojet
https://en.wikipedia.org/wiki/Turbojet
(section 4 Net thrust: F=ṁ(Vj-V) )
, where "Vj is the speed of the jet (the exhaust plume)"  and "V" (air) speed right before air enters the inlet.

mass flow rate
https://en.wikipedia.org/wiki/Mass_flow_rate
(is the mass of a substance [air here] which passes per unit of time; ṁ (pronounced "m-dot") )

Take notice, from the figures of this Wiki page, that a turbojet has no bypass. In other words, a turbojet uses all air drawn in by the fan (at the inset) to burn fuel.
(ii) turbofan:
(A) "The hot exhaust passes through the core and fan turbines and then out the nozzle, as in a basic turbojet. The rest of the incoming air passes through the fan and bypasses, or goes around the engine, just like the air through a propeller. The air that goes through the fan [and hence the bypass] has a velocity that is slightly increased from free stream [the air right before inlet]. * * * Because the fan is enclosed by the inlet and is composed of many blades, it can operate efficiently at higher speeds than a simple propeller. That is why turbofans are found on high speed transports and propellers are used on low speed transports. Low bypass ratio turbofans are still more fuel efficient than basic turbojets. Many modern fighter planes actually use low bypass ratio turbofans equipped with afterburners. They can then cruise efficiently but still have high thrust when dogfighting."  NASA's Glenn Research Center on "turbofan engine."
(B) turbofan
https://en.wikipedia.org/wiki/Turbofan
(The ratio of the mass-flow of air bypassing the engine core divided by the mass-flow of air passing through the core is referred to as the bypass ratio; section 1.3 Thrust: The net thrust F=ṁhevhe-ṁv+BPR(ṁcvf)
, where ṁhe and vhe are mass flow rate and velocity of hot exhaust;
ṁ0 and v0 are mass flow rate and velocity of air right before inlet (0 is zero, not letter o).

The "BPR(ṁcvf)" is easy to understand if you recall BPR is equal to ṁf/ṁc. Therefore "BPR(ṁcvf)" is nothing but "(ṁcvf)" which is the momentum of bypass air flow.
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5#
 楼主| 发表于 12-26-2018 15:47:16 | 只看该作者
(g)
(i) Turboprop Thrust. NASA's GRC, undated
https://www.grc.nasa.gov/www/k-12/airplane/turbprp.html
("Propellers are very efficient and can use nearly any kind of engine to turn the prop. General aviation aircraft use an internal combustion engine to turn the propeller. In the turboprop, a gas turbine core is used. * * * However, at the exit of the main turbine the hot exhaust gas is passed through an additional turbine, shown in green on the schematic, before entering the nozzle. Unlike a basic turbojet, most of the energy of the exhaust is used to turn this additional turbine. The turbine is attached to an additional drive shaft which passes through the [immobile] core shaft [that is, only drive shaft revolve but not core shaft] and is connected to a gear box. The gear box is then connected to a propeller that produces most of the thrust. The exhaust velocity of the core is low and contributes little thrust because most of the energy of the core exhaust has gone into turning the drive shaft")

The net thrust F=ṁ0(v1-v0) + ṁe(ve-v1)
, where ṁ0 is mass flow rate right before inlet, v1 the air velocity right after the fan, and ve air velocity of (hot) exhaust right after the second turbine.
(A) "Turboprops can have bypass ratios up to 50-100  although the propulsion airflow is less clearly defined for [uncased] propellers than for [ducted] fans."  en.wikipedia.org for Turboprop (quotations omitted),
(B) A ducted fan is a fan in a circular case. The case is narcelle, and needs to be carefully designed with an eye on aerodynamics.

nacelle
https://en.wikipedia.org/wiki/Nacelle

nacelle (n; from Modern French [noun feminine of the same spelling], literally, small boat, from Late Latin [noun feminine] navicella, diminutive of Latin [noun feminine] navis ship)
https://www.merriam-webster.com/dictionary/nacelle
(ii) David Firel Schaller, A Technique for Shape optimization of Ducted Fans. Department of Aerospace Engineering, Iowa State University, 2007, at pages 1-2 (thesis for master of science)
https://lib.dr.iastate.edu/cgi/v ... 798&context=rtd
("1.1 Ducted Fan History[:] Ducted fans have been modeled and studied extensively and have been used in marine applications, rotorcraft / VSTOL [as in F-35B] applications and HVAC. * * * In the 1940s and 50s [Stanley] Hiller pioneered a flying platform using a fan situated within annular wings. It was found that the airfoil duct accelerated airflow into the rotor. Additionally, Hiller found that the duct could generate 40% more thrust than a[n uncased] propeller of the same diameter. Hiller's aircraftm the Model 1031 used coaxially mounted rotors within a single fiberglass duct")(citations omitted)

Hiller Model 1031-A-1 Flying Platform. National Air and Space Museum, Smithsonian Institution, undated
https://airandspace.si.edu/colle ... 1-1-flying-platform
("1 of 7")

You have to click the arrow on the right margin to proceed.
(iii) ducted fan
https://en.wikipedia.org/wiki/Ducted_fan
(section 2 advantages: By reducing propeller blade tip losses, the ducted fan is more efficient in producing thrust than a conventional propeller of similar diameter,)
(iv) That is due to vortex drag at the tip of propeller and fixed wings alike. For the latter, see Vortex Drag. Smithsonian National Air and Space Museum, undated (video).
https://howthingsfly.si.edu/aerodynamics/vortex-drag

A winglet alleviates the issue in fixed-winged aircraft.
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