WO2004013473A2 - Moteur a turbine a tourbillon - Google Patents

Moteur a turbine a tourbillon Download PDF

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Publication number
WO2004013473A2
WO2004013473A2 PCT/US2003/021732 US0321732W WO2004013473A2 WO 2004013473 A2 WO2004013473 A2 WO 2004013473A2 US 0321732 W US0321732 W US 0321732W WO 2004013473 A2 WO2004013473 A2 WO 2004013473A2
Authority
WO
WIPO (PCT)
Prior art keywords
air
vortex flow
vortex
engine
turbine
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/US2003/021732
Other languages
English (en)
Other versions
WO2004013473A3 (fr
Inventor
David A. Platts
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.)
University of California Berkeley
University of California San Diego UCSD
Original Assignee
University of California Berkeley
University of California San Diego UCSD
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 University of California Berkeley, University of California San Diego UCSD filed Critical University of California Berkeley
Priority to AU2003281869A priority Critical patent/AU2003281869A1/en
Publication of WO2004013473A2 publication Critical patent/WO2004013473A2/fr
Publication of WO2004013473A3 publication Critical patent/WO2004013473A3/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
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/045—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor having compressor and turbine passages in a single rotor-module
    • F02C3/05—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor having compressor and turbine passages in a single rotor-module the compressor and the turbine being of the radial flow type
    • 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
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/14—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/127—Vortex generators, turbulators, or the like, for mixing
    • 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
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the present invention generally relates to turbine engines, and, more specifically, relates to an improved vortex flow turbine engine.
  • This invention was made with Government support under Contract No. W-7405-ENG-36 awarded by the U.S. Department of Energy. The Government has certain rights in the invention.
  • Turbine engines are in use in many fields, but are particularly applicable where light, compact, low maintenance power sources are needed. Aircraft engines, and electricity generation are prominent uses of gas turbine engines. Gas turbines and related systems have been in use and described in the literature for a number of years. Such systems include a compressor for compressing ambient air, a diffuser to convert some of the remaining kinetic energy from the compressor to pressure, a combustor to heat the compressed air, a device to lower the temperature of the combustion gasses, a set of nozzle guide vanes to add kinetic energy to the gasses before introduction to the turbine in which the heated gasses from the combustor are expanded to produce mechanical power. Some of this power is used to drive the compressor.
  • Power is extracted from the engine by using the turbine exhaust gases directly to produce thrust or to drive a turbine which produces mechanical power.
  • Mechanical power can also be extracted directly from the engine shaft, or obtained from the engine in other ways. In electricity generation the mechanical power is used to turn a generator.
  • the gases from the combustor section must be lowered in temperature from the temperature at which the gas has burned. This lowering of temperature is usually accomplished in the rear portion of the combustion chamber by admitting unheated air from the compressor.
  • the combustion chambers of conventional turbine engines have been developed to provide good combustion efficiency with recent efforts being devoted to reducing the production of NOx. Many of these combustion chambers use some swirl or vortex action to achieve these results.
  • the strong vortex provides a kinetic radial pressure gradient as opposed to the largely static pressure of conventional designs.
  • the methods used to provide good combustion efficiency and low NOx production in conventional combustion chambers can still be used in the vortex chamber. In fact even more kinetic energy is available to accomplish these goals.
  • the vortex chamber also has the option of controlling the vortex rotation and recirculation by simply changing the diameter of the chamber along its length.
  • the present invention provides apparatus and method for improving the efficiency of turbines. One way that it does this is by the elimination of certain components. This elimination of components eliminates the losses associated with those components, making it more efficient, lighter, and less expensive to manufacture.
  • a turbine engine having increased efficiency and fewer components comprises a generally cylindrical engine housing defining a longitudinal axis with a centrifugal compressor rotor mounted to a shaft in the engine housing along the longitudinal axis for creating a vortex flow of air flowing through the engine housing and defining a low pressure area along the longitudinal axis.
  • At least one fuel inlet in the engine housing inserts fuel into the vortex flow of air and creates a flame front along the low pressure area to heat the vortex flow of air; and a turbine rotor is mounted to the shaft for receiving the vortex flow of heated air and spinning.
  • a turbine engine having increased efficiency and fewer components comprises an engine housing defining a longitudinal axis with a centrifugal compressor rotor mounted to a shaft in the engine housing along the longitudinal axis for creating a vortex flow of air flowing through the engine housing and defining a low pressure area along the longitudinal axis.
  • At least one fuel inlet in the engine housing inserts fuel into the low pressure area of the vortex flow of air and creates a flame front along the low pressure area to heat the vortex flow of air and a turbine rotor mounted to the shaft for receiving the vortex flow of heated air and spinning.
  • FIGURE 1 is a cross-sectional side view of a prior art turbine.
  • FIGURE 2 is a cross-sectional side view of a turbine engine according to the present invention.
  • the present invention provides turbine engines that feature more efficient operation, lighter weight, reduced parts count, and no backpressure for the fuel to overcome through the use of a vortex flow of air.
  • the invention is understood most easily through reference to the drawings.
  • FIG. 1 there can be seen a cross-sectional side view of a conventional prior art turbine engine with a radial compressor.
  • air is entering centrifugal compressor rotor H, where it is compressed and given a velocity that is tangential to the longitudinal axis of the engine.
  • the compressed air then enters diffuser 12 where its pressure if further increased by way of conversion of the tangential velocity into pressure.
  • the pressurized air then enters combustion chamber 1_3 where it is combined with fuel and burned and then combined with more air to reduce its temperature to a level that will not melt turbine blades 14.
  • the hot gas is then spun up by nozzle guide vanes 15 and used to spin turbine blades 14, which powers centrifugal compressor rotor 11 via shaft 14b.
  • turbine engine housing 3 defines an air inlet 31a, a combustion chamber wall 31 b and an exhaust 31 c.
  • centrifugal compressor 32 connected by shaft 34 to turbine rotor 35.
  • centrifugal compressor 32 creates a vortical flow of air that defines low pressure area 32a.
  • the vortical flow of air from centrifugal compressor 32 encounters fuel introduced from fuel inlet 32b and is heated as the fuel burns in vortex combustion chamber 33.
  • the vortical flow of combustion gasses passes through turbine rotor 35, causing it to turn.
  • the ignited fuel burns along the interface with low-pressure area 32a.
  • the air from radial compressor 32 is introduced directly to the vortex combustion chamber 33 without use of a diffuser, a lossy component used by the prior art to convert kinetic energy to pressure energy.
  • radial compressor 32 The profile of radial compressor 32 is designed to produce a highly kinetic swirl flow unlike many present designs that have severely backswept blades whose output has more pressure energy and less kinetic energy. In general, radial compressor blades are stronger and more efficient than the backswept blades.
  • the trapped swirling flow of air produces a radial pressure gradient, which can range from sub atmospheric in the center of low-pressure region 32a to high pressure next to the wall of turbine engine housing 3 . .
  • the fuel is introduced into low-pressure region 32a, thus eliminating the need for a fuel pump when used with low pressure gaseous fuel, one fuel available in most homes.
  • the rotational velocity of the air in vortex combustion chamber 33 is controlled by the diameter of the combustion chamber wall 31 b Thus variations in the diameter produce pressure variations and flows along the axis of turbine engine housing 3 _. In this manner flow reversals for fuel mixing and burning can be created in the combustion chamber.
  • combustion chamber wall 31b is varied in this embodiment by vortex control structures 36.
  • vortex control structures 36 Although shown in Figure 3 as convex vortex control structures 36, narrowing the diameter of combustion chamber wall 31b, vortex control structures 36 could as well be concave, increasing the diameter of combustion chamber wall 31 b at predetermined locations, or any desired combination of convex and concave vortex control structures 36 located at desired positions.
  • Additional vanes and blockages 37 can be used to produce faster mixing and combustion, but these can be in the low velocity low pressure flow close to the axis extending out into high velocity flow only enough to provide the energy needed for mixing, combustion, and dilution.
  • the combustion chamber wall 31 b of vortex combustion chamber 33 is protected and cooled by the high velocity air flow on the outside of the vortex. The losses caused by having to force all the air through holes in a conventional combustion chamber are eliminated by the present invention.
  • Turbine rotor 35 can be axial, radial, or anything in between.
  • the undulations introduced by vortex control structures 36 serve to control the vortex burning and increase the spin of the vortex before it encounters turbine 35.
  • Placing vortex control structures 37 near fuel inlet 31b could be used to trip the turbulent burning layer, if needed. Use of any vortex control structures 37 may not be required. It is necessary that a determination be made in practice of the present invention as to whether application of vortex control structures 37 is advantageous.
  • One of the important benefits of the present invention is the rapid fuel burning brought about by the vortical flow of air which can provide energy for highly turbulent mixing. Turbulent mixing can also be used to quickly lower the temperature of the combustion products to reduce NOx generation, thereby reducing the pollution from operation of the present invention.
  • the invention also creates a low-pressure area for the introduction of fuel, eliminating the need high- pressure introduction of fuel.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

L'invention a trait à un moteur à turbine présentant une efficacité accrue et comportant un nombre réduit de pièces. Un logement de moteur définit un axe longitudinal, et un rotor de compresseur centrifuge est monté sur un arbre dans le logement le long de l'axe longitudinal, afin que soit généré un écoulement tourbillonnaire d'air s'écoulant à travers le logement, ledit écoulement définissant une zone de basse pression le long de l'axe longitudinal. Au moins un orifice d'entrée de carburant est placé dans le logement de moteur, ledit orifice d'entrée servant à l'introduction du combustible dans l'écoulement tourbillonnaire d'air, et à la génération d'un front de flamme le long de la zone de basse pression, afin de chauffer l'écoulement tourbillonnaire d'air. Un rotor de turbine, monté sur l'arbre, est destiné à recevoir l'écoulement tourbillonnaire d'air chauffé et à tourner.
PCT/US2003/021732 2002-07-23 2003-07-14 Moteur a turbine a tourbillon Ceased WO2004013473A2 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AU2003281869A AU2003281869A1 (en) 2002-07-23 2003-07-14 Vortex turbine engine

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US20242102A 2002-07-23 2002-07-23
US10/202,421 2002-07-23

Publications (2)

Publication Number Publication Date
WO2004013473A2 true WO2004013473A2 (fr) 2004-02-12
WO2004013473A3 WO2004013473A3 (fr) 2004-07-08

Family

ID=31494244

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US2003/021732 Ceased WO2004013473A2 (fr) 2002-07-23 2003-07-14 Moteur a turbine a tourbillon

Country Status (2)

Country Link
AU (1) AU2003281869A1 (fr)
WO (1) WO2004013473A2 (fr)

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3126703A (en) * 1959-12-24 1964-03-31 Gas turbine power plant with rotary fuel atomization

Also Published As

Publication number Publication date
WO2004013473A3 (fr) 2004-07-08
AU2003281869A1 (en) 2004-02-23
AU2003281869A8 (en) 2004-02-23

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