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WO1983001277A1 - Groupe propulseur compact avec cycle thermique efficient - Google Patents

Groupe propulseur compact avec cycle thermique efficient Download PDF

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Publication number
WO1983001277A1
WO1983001277A1 PCT/US1981/001336 US8101336W WO8301277A1 WO 1983001277 A1 WO1983001277 A1 WO 1983001277A1 US 8101336 W US8101336 W US 8101336W WO 8301277 A1 WO8301277 A1 WO 8301277A1
Authority
WO
WIPO (PCT)
Prior art keywords
compressor
power plant
turbine
gaseous medium
medium
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Ceased
Application number
PCT/US1981/001336
Other languages
English (en)
Inventor
Alexander Goloff
John M Clarke
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Individual
Original Assignee
Individual
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Individual filed Critical Individual
Priority to PCT/US1981/001336 priority Critical patent/WO1983001277A1/fr
Publication of WO1983001277A1 publication Critical patent/WO1983001277A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C5/00—Gas-turbine plants characterised by the working fluid being generated by intermittent combustion
    • F02C5/06—Gas-turbine plants characterised by the working fluid being generated by intermittent combustion the working fluid being generated in an internal-combustion gas generated of the positive-displacement type having essentially no mechanical power output
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02G—HOT GAS OR COMBUSTION-PRODUCT POSITIVE-DISPLACEMENT ENGINE PLANTS; USE OF WASTE HEAT OF COMBUSTION ENGINES; NOT OTHERWISE PROVIDED FOR
    • F02G1/00—Hot gas positive-displacement engine plants
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B1/00—Engines characterised by fuel-air mixture compression
    • F02B1/02—Engines characterised by fuel-air mixture compression with positive ignition
    • F02B1/04—Engines characterised by fuel-air mixture compression with positive ignition with fuel-air mixture admission into cylinder
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T10/00—Road transport of goods or passengers
    • Y02T10/10—Internal combustion engine [ICE] based vehicles
    • Y02T10/12—Improving ICE efficiencies

Definitions

  • This invention relates to a power plant of relatively small si2e and yet which can operate on what is basically an Atkinson cycle.
  • Turbine engines operate on the "Brayton" cycle. Each, of these cycles has a certain theoretical efficiency which is dependent upon design parameters associated with the particular mechanism involved. Eac of the foregoing cycles also has points of inef ⁇ ficiency which may arise out of either theoretical or practical considerations.
  • maximum temperatures allowable in turbines are on the order of 1700 F. At temperatures appreciably in excess of 1700 F. , thermal expansion as well as growth due to centrifugal force may cause interference between the turbine blades and the housing which results in the destruction of the machine.
  • Diesel and Brayton cycles proposals have been made whereby efficiencies not obtainable with any of above- mentioned cycles can be obtained by selected use of the best characteristics of the Brayton cycle and of the Otto or Diesel cycles.
  • An example is a turbocompound internal combustion engine.
  • Such an engine consists of a positive displacement mechanism such as a reciprocating or rotary engine operating on the Otto or Diesel cycle as desired. Exhaust gases from the positive displacement mechanism are not discharged directly to atomosphere as in conventional Otto or Diesel cycle engine operation, but rather, expanded further in turbines which drive a compressor which compresses the incoming gaseous medium and also add work to the output shaft thereby recovering work from • the exhausting gaseous medium.
  • the initial expansion occurring in the positive displacement mechanism results in a reduction in the temperature of the working fluid to a sufficiently low level that it may enter the turbine to be expanded further therein without heating the turbine to an undesirable high temperature.
  • This proposal utilizes a combination of a free piston engine/compressor plus a turbine wherein heat addition occurs when the free piston engine/compressor is at minimum volume.
  • a cycle in which near-isentropic expansion occurs over the full maximum to minimum pressure ratio after combustion at constant volume is generally known as an "Atkinson" cycle. This cycle increases efficiency relative to Otto, Diesel or Brayton cycles having the same compression ratio.
  • the present invention is directed to overcoming one or more of the problems set forth above.
  • a power plant for operation on what may be generally termed an Atkinson type cycle.
  • the power plant includes a compressor for compressing a working fluid.
  • a positive displacement mechanism receives the compressed working fluid from the compressor and adds heat thereto at substantially maximum volume and thereafter displaces the heated compressed medium from the mechanism.
  • An expander is provided for receiving the heated, compressed medium and for expanding the . medium to recover useful work therefrom and to drive the compressor and the positive displacement mechanism.
  • Another aspect of the invention contemplates the use of other components to further increase the efficiency of the power plant while generally operating on the Atkinson cycle, albeit somewhat modified due to the presence of such other components.
  • Fig. 1 is a diagrammatic view of a power plant made according to one embodiment of -the invention.
  • Fig. 2 is a plot of various power plant opera- tional cycles of pressure versus percent volume.
  • FIG. 1 An exemplary embodiment of a power plant made according to the invention is illustrated in Fig. 1 and is seen to include a compressor 10 having an inlet shown schematically at 12 and an outlet 14. A gaseous working medium, usually air, is admitted to the compres ⁇ sor 10 at the inlet 12 and is compressed therein to flow therefrom out of the outlet 14.
  • a gaseous working medium usually air
  • the compressor 10 may be provided with interstage cooling means 16 of a conventional nature to enhance system efficiency by assuring that compression of the working medium in the compressor 10 approximates isentropic compression as nearly as possible.
  • the outlet 14 is in fluid communication with the interior of a combination recuperator-surge tank 18.
  • the recuperator-surge tank 18 includes an outlet 20 through which the compressed working fluid may exit for purposes to be seen as well as an interior heat exchanger 22.
  • the heat exchanger 22 has an inlet 24 for receiving heated exhaust gases from the power plant. Such gases, after being cooled in the recupera ⁇ tor-surge tank 18 exit the same via an outlet 26 from the heat exchanger 22.
  • a positive displacement mechanism 30 has an inlet 32 connected to the outlet 20 of the recuperator- surge tank 18. As seen in Fig.
  • the positive dis ⁇ placement mechanism 30 is of the trochoidal type and includes an operating .chamber wall * 34 provided with a single lobe 36 between the inlet port 32 and an outlet port 38.
  • a two apexed rotor 40 is journalled for rota ⁇ tion and translation on a main shaft 42 and includes seals 44 on its apexes.
  • the construction is generally that of a two stroke trochoidal engine, whether epitro- choidal or hypotrochoidal with the exception that ports 32 and 38. have been relocated about the periphery of the wall 34 as has a fuel injector 46 from their conventional locations. Specifically, in the mechanism 30 as illus ⁇ trated in Fig. 1,.
  • heat addition is to take place when the components are in the maximum volume position as illustrated in Fig. 1. This is in contrast to the usual heat addition occurring at minimum, volume and this ac- counts for the relocation of the ports ' 32 and 38 and the fuel injector 46 from thosein a- typical two stroke tro ⁇ choidal engine.
  • the invention is not limited to use of a tro ⁇ choidal mechanism.
  • the general configuration of a typical two stroke slant axis rotary mechanism could likewise be used.
  • a reciprocating mechanism. similar to a valved, two stroke engine could be utilized with fuel being injected when the piston reaches, bottom dead center.
  • the components are in a maximum volume position and at this time, both the inlet port 32 and the outlet port 38 are closed. Heat is added at this time through the burning of fuel and continued rotation and translation of the rotor 40 in the direction of an arrow 48 will maintain the inllet port 32 in isolation from the now opening outlet port 38.
  • the heat addition at this time will cause a rapid increase in pressure of the working fluid and the working fluid will be displaced by the.rotor 40 from the mechanism out of the outlet port 38. It will be appreciated that the heat addition is substantially at constant volume in that at the time of fuel injection and com ⁇ bustion, the volume of the mechanism 30 will be sub- stantially constant at its maximum.
  • Heated compressed working fluid exiting the port 38 is conducted to a receiver or surge tank 50 and then to a turbine, generally designated 52 which may or may not have multiple stages such as the multi ⁇ ple stages 54 and 56 illustrated.
  • the expanding medium drives the turbine 52 and its output shaft 58. Useful work may be taken off of the rotating shaft 58.
  • the shaft 58 is coupled to the main shaft 42 of the positive displacement mechanism 30 to drive the same.
  • the working medium is . expanded substantially to atmospheric pressure and exits the. same through an outlet 62 which is connected to the inlet 24 for the heat exchanger 22 and the re ⁇ cuperator-surge tank 18.
  • the gas will ultimately exit via the outlet 26 but only after giving up any residual heat within the recuperator-surge tank 18 to incoming compressed working fluid received from the compressor 10.
  • recuperator-surge tank 18 provides a surge tank function
  • the turbine 52 will be of the variable geometry type so that the inlet pressure of the turbine 5-2 is maintained at a value equal to the pressure of the working fluid as is dis ⁇ charged from the surge tank 50. This may be accom ⁇ plished, for example, by utilizing variable nozzles in the turbine 52 which are suitably controlled in the man- ner disclosed in the commonly assigned U. S. Patent
  • the amount of fuel added by the injector 46 is such as to increase the temperature of the working fluid preferably only to a value on the order of the maximum operating temperature of the turbine 52.
  • the temperature of the working medium exiting the port ' 38 may be slightly in excess of the maximum operating temperature of the turbine 52 as there will be some heat loss incurred in flowing from the outlet 38 to- .the turbine 52.
  • the power plant operates generally on the so-called Atkinson cycle. Air at ambient temperature is compressed from point A to point B as shown in Fig. 2. This occurs in the compressor 10. Heat is then added at constant volume in the mechanism 30 as shown by the line BC such that the temperature of the heated, compressed working flui at point C is not sub ⁇ stantially in excess of the maximum working temperature of the turbine 52. Expansion of the working fluid then occurs in the turbine 52 and is shown, by the line CD while heat rejection is shown by the line DA. If a straight Brayton cycle operation were util ⁇ ized, heat addition would occur at a constant pressure along the line BC .
  • recuperator-surge tank 18 may be utilized in a system wherein the compressor 10 is not provided with interstage cooling in which case it would follow the diagram ABE'F'G'A, which cycle will be more efficient than the straight Atkinson cycle ABCDA but less efficient than the modified Atkinson cycle AEE'F'G'A.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)

Abstract

Un groupe propulseur pouvant fonctionner sensiblement selon un cycle du type Atkinson comprend un compresseur (10) pour comprimer un milieu gazeux. Un mécanisme à déplacement positif (30) sert à recevoir le milieu gazeux comprimé provenant du compresseur et à ajouter de la chaleur jusqu'à une température limite dans un volume sensiblement maximum et à déplacer ensuite du mécanisme (30) le milieu gazeux comprimé chauffé. Une turbine (52) pouvant fonctionner en continu à une température égale ou inférieure à la température limite reçoit le milieu gazeux comprimé chauffé qui se détend pour fournir du travail utile et pour entraîner le mécanisme (30) et le compresseur (10). L'addition de chaleur dans le mécanisme (30) lorsque celui-ci présente son volume maximum permet au mécanisme (30) d'avoir une taille relativement réduite et permet d'obtenir un groupe propulseur compact qui fonctionne avec le rendement propre du cycle Atkinson.
PCT/US1981/001336 1981-10-02 1981-10-02 Groupe propulseur compact avec cycle thermique efficient Ceased WO1983001277A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PCT/US1981/001336 WO1983001277A1 (fr) 1981-10-02 1981-10-02 Groupe propulseur compact avec cycle thermique efficient

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/US1981/001336 WO1983001277A1 (fr) 1981-10-02 1981-10-02 Groupe propulseur compact avec cycle thermique efficient

Publications (1)

Publication Number Publication Date
WO1983001277A1 true WO1983001277A1 (fr) 1983-04-14

Family

ID=22161461

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US1981/001336 Ceased WO1983001277A1 (fr) 1981-10-02 1981-10-02 Groupe propulseur compact avec cycle thermique efficient

Country Status (1)

Country Link
WO (1) WO1983001277A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2730274A1 (fr) * 1995-02-08 1996-08-09 Menioux Claude Charles Felix Moteur a pistons rotatifs et combustion externe
GB2468143A (en) * 2009-02-26 2010-09-01 Univ Cranfield Gas generator comprising a positive displacement gas motor with a controlled outlet valve

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1137328A (en) * 1907-07-18 1915-04-27 Irving C Jennings Internal-combustion generator.
US1332427A (en) * 1919-01-21 1920-03-02 Cooper Mckee Rotary engine
US3222864A (en) * 1962-12-31 1965-12-14 Garrett Corp Gas turbine engine fixed boundary recuperator
US3417564A (en) * 1967-04-19 1968-12-24 John G. Call Jet engine with relatively rotatable combustion means, intake manifold and exhaust manifold
DE2426700A1 (de) * 1974-06-01 1975-12-11 Georg Dunas Rotationskolbenmotor
US4241576A (en) * 1979-01-15 1980-12-30 Gertz David C Gas turbine engine

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1137328A (en) * 1907-07-18 1915-04-27 Irving C Jennings Internal-combustion generator.
US1332427A (en) * 1919-01-21 1920-03-02 Cooper Mckee Rotary engine
US3222864A (en) * 1962-12-31 1965-12-14 Garrett Corp Gas turbine engine fixed boundary recuperator
US3417564A (en) * 1967-04-19 1968-12-24 John G. Call Jet engine with relatively rotatable combustion means, intake manifold and exhaust manifold
DE2426700A1 (de) * 1974-06-01 1975-12-11 Georg Dunas Rotationskolbenmotor
US4241576A (en) * 1979-01-15 1980-12-30 Gertz David C Gas turbine engine

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2730274A1 (fr) * 1995-02-08 1996-08-09 Menioux Claude Charles Felix Moteur a pistons rotatifs et combustion externe
GB2468143A (en) * 2009-02-26 2010-09-01 Univ Cranfield Gas generator comprising a positive displacement gas motor with a controlled outlet valve

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