WO2013023147A1 - Chambre de combustion - Google Patents

Chambre de combustion Download PDF

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Publication number
WO2013023147A1
WO2013023147A1 PCT/US2012/050349 US2012050349W WO2013023147A1 WO 2013023147 A1 WO2013023147 A1 WO 2013023147A1 US 2012050349 W US2012050349 W US 2012050349W WO 2013023147 A1 WO2013023147 A1 WO 2013023147A1
Authority
WO
WIPO (PCT)
Prior art keywords
air
fuel
tube
combustor
combustion chamber
Prior art date
Application number
PCT/US2012/050349
Other languages
English (en)
Inventor
Michael J. O'donnell
Original Assignee
Beckett Gas, Inc.
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 Beckett Gas, Inc. filed Critical Beckett Gas, Inc.
Priority to EP12822757.6A priority Critical patent/EP2742292A4/fr
Priority to CA2844693A priority patent/CA2844693A1/fr
Priority to CN201280050137.7A priority patent/CN103998867A/zh
Priority to US14/238,067 priority patent/US20140190178A1/en
Publication of WO2013023147A1 publication Critical patent/WO2013023147A1/fr

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/06—Arrangement of apertures along the flame tube
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/38—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising rotary fuel injection means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/50—Combustion chambers comprising an annular flame tube within an annular casing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/58—Cyclone or vortex type combustion chambers
    • 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 invention relates to a fuel burner and, in particular, relates to a combustor for a gas turbine engine or heating appliance that imparts a centrifugal force upon combustion air or a combination of air and fuel.
  • Gas turbines also referred to as jet engines, are rotary engines that extract energy from a flow of combustion gas. They have an upstream compressor coupled to a downstream turbine with a combustion chamber in between. There are many different variations of gas turbines, but they all use the same basic principal.
  • Jet aircraft are usually powered by turbojet or turbofan engines.
  • a turbojet engine is a gas turbine engine that works by compressing air with an inlet and a compressor, mixing fuel with the compressed air, burning the mixture in the combustor, and then passing the hot, high pressure gas through a turbine and a nozzle.
  • the compressor is powered by the turbine, which extracts energy from the expanding gas passing through it.
  • the engine converts energy in the fuel to kinetic energy in the exhaust, producing thrust. All the air ingested by the inlet passes through the compressor, combustor, and turbine.
  • a turbofan engine is very similar to a turbojet except that it also contains a fan at the front of the compressor section. Like the compressor, the fan is also powered by the turbine section of the engine. Unlike the turbojet, some of the flow accelerated by the fan bypasses the combustor and is exhausted through a nozzle. The bypassed flow is at a lower velocity, but a higher mass, making thrust produced by the fan more efficient than thrust produced by the core.
  • Turbofans are generally more efficient than turbojets at subsonic speeds, but they have a larger frontal area which generates more drag at higher speeds.
  • Turboprop engines are jet engine derivatives that extract work from the hot- exhaust jet to turn a rotating shaft, which is then used to spin a propeller to produce additional thrust.
  • Turboprops generally have better performance than turbojets or additional thrust
  • Turboprops generally have better performance than turbojets or turbofans at low speeds where propeller efficiency is high, but become increasingly noisy and inefficient at high speeds.
  • Turboshaft engines are very similar to turboprops, differing in that nearly all of the energy in the exhaust is extracted to spin the rotating shaft. Turboshaft engines are used for stationary power generating plants as well as other applications.
  • the present invention provides a new and improved method of combustion and a combustor or burner that can be used in a jet engine, as well as other heating burner applications.
  • the combustor is shown as it would be used with a jet engine of the type that includes a compressor portion and a turbine portion.
  • the jet engine includes a compressor portion and turbine portion.
  • the combustor includes a longitudinally extending tube having a central axis, which is positioned to receive air that is charged by the compressor portion.
  • the outer tube has an outer surface and an inner surface.
  • An inner tube is positioned within the outer tube and includes an associated outer surface that is spaced from the inner surface of the outer tube, thereby defining a passage that may be a combustion chamber where a fuel mixture can be at least partially combusted.
  • the outer tube includes fluid directing structure for communicating at least some of the air discharged by the compressor portion to a combustion chamber passage that is defined between the inner surface of the outer tube and the outer surface of the inner tube.
  • the fluid directing structure directs air in a direction offset from the central axis of the outer tube, thereby causing rotation of the air about the central axis.
  • At least one fuel supply member directly or indirectly supplies fuel to the combustion chamber passage in order to form a rotating or swirling fuel air mixture in the combustion chamber passage.
  • the rotating fuel mixture in the combustion chamber passage may be completely or partially burned in the combustion chamber passage.
  • the inner tube also includes associated fluid directing structure for communicating air it receives from the compressor portion to the combustion chamber passage.
  • the associated fluid directing structure directs the air in a direction that is also offset from the central axis.
  • the fuel member communicates directly with the combustion chamber passage and directly supplies fuel to the chamber passage where it is mixed with the compressor air to form a rotating/swirling combustible fuel/air mixture.
  • the fuel member premixes the fuel with some compressor air and then supplies the premixed fuel and air to the combustion chamber passage where it is mixed with the rotating compressor air (or fuel/air mixture) already delivered to the combustion chamber passage.
  • the fuel member discharges fuel into a stream of air discharged by the compressor portion as it flows towards the combustor.
  • both fuel and compressor air flow through the fluid directing structure of the outer and or inner tubes into the combustion chamber passage.
  • the outer and inner tubes are arranged such that their respective axes are coincident.
  • the axes of the inner and outer tubes are coincident with a rotation axis defined by the compressor portion.
  • the fluid directing structure includes a plurality of openings and a guide associated with each opening, the guides being angled relative to a tube surface for imparting a radial rotation to the air about the central axis.
  • the guides are arranged in a series of rows that extend around the periphery of the outer tube.
  • me inner tube has a similar fluid directing structure.
  • the fluid directing structure includes a series of steps formed in the outer tube, the steps including openings for directing the air into the combustion chamber passage in a direction that causes rotation or swirling of the mixture radially about the central axis.
  • each step has an L-shape including a first member and a second member including the openings for directing the air, such that the openings of one step direct the air across the adjoining step to impart rotation to the mixture.
  • the fluid directing structure includes a plurality of openings that each extend from the outer surface of the outer tube to the inner surface, each opening extending through the outer tube at a relative angle to an axis extending normal to the outer surface of the inner tube and through the central axis.
  • the outer tube includes a plurality of second openings that each extend from the outer surface of the outer tube to the inner surface in a direction extending to the central axis.
  • the inner tube includes similar fluid directing structure.
  • die outer tube is formed as a series of overlapping arcuate plates that define the fluid directing structure, each plate having a corrugated profile and having a series of passages through which the air is directed into the combustion chamber passage.
  • the corrugated profile includes a plurality of alternating peaks and valleys and, preferably, the overlapping plates are longitudinally and radially offset from one another, such that the peaks of one plate are positioned between the peaks of adjacent plates.
  • each plate directs the air in a direction that extends substantially parallel to the adjoining plate to impart rotation to the mixture.
  • the inner tube of the combustor includes a first end that communicates with air discharged by the compressor portion and a second end having an end wall for closing the second end of the inner tube in a gas tight manner.
  • the fluid directing structure associated with the inner and outer tubes provides the only fluid path to the combustion chamber passage.
  • the rotating mixture is radially layered within the combustion chamber passage.
  • the combustor includes a tube having a central axis that is located intermediate the compressor portion and the turbine portion and has an outer and inner surface.
  • Fluid directing structure is formed on the tube, including passages extending from the outer surface to the inner surface.
  • the inner surface of the tube defines a combustion chamber.
  • a passage communicates air discharged by the compressor portion with the outer surface of the tube.
  • the fluid directing structure directs the compressor air at an angle offset from the central axis of the tube, thereby causing rotation of compressor air in the combustion chamber.
  • a fuel member supplies fuel or a mixture of fuel and air, directly or indirectly, to the combustion chamber.
  • a spaced apart continuous wall surrounds the tube, thereby defining at least a portion of the passage for communicating air to the outer surface of the tube.
  • the jet engine includes a plurality of these alternate combustors mat are spatially arranged around an axis of rotation defined by the compressor portion.
  • An object of the present invention is to provide a jet engine combustor in which air or fuel and air are forced through fluid directing structures to cause swirling and/or rotation of the air/fuel mixture about the axis of the combustor.
  • Fig. 1 is a schematic illustration of a combustor for use in a jet engine in accordance with an aspect of the present invention
  • Fig. 2 A is a section view taken along line 2A-2 A of Fig. I ;
  • Fig. 2B is a section view taken along line 2B-2B of Fig. 1;
  • Fig. 3 A is an enlarged view of a portion of a fluid directing structure
  • Fig. 3B is a section view of Fig. 3 A taken along line 3B-3B;
  • FIGs. 4A-4D are enlarged views of portions of alternative fluid directing structure in accordance with the present invention.
  • Fig. 5 is a schematic illustration of an alternative combustor for use in a jet engine in accordance with another aspect of the present invention.
  • Fig. 6A is a section view taken along line 6A-6A of Fig. S;
  • Fig. 7 is a schematic illustration of an alternative combustor for use in a jet engine in accordance with another aspect of the present invention.
  • Fig. 8A is a section view taken along line 8A-8A of Fig. 7;
  • Fig. 8B is a section view taken along line 8B-8B of Fig. 7;
  • Fig. 9 is a schematic illustration of an alternative combustor for use in a jet engine in accordance with another aspect of the present invention.
  • Fig. 10 is a section view taken along line 10- 10 of Fig. 9, and;
  • Fig. 1 1 is a section view taken along line 11-11 of Fig. 10.
  • the invention relates to a fuel burner and, in particular, relates to a combustor for a gas turbine engine that imparts a centrifugal force upon combustion air or a combination of air and fuel.
  • a gas turbine engine that imparts a centrifugal force upon combustion air or a combination of air and fuel.
  • Figs. 1 -2B illustrate a combustor 240 for use in a jet engine 200 in accordance with an embodiment of the present invention.
  • the jet engine 200 extends along an axis 202 and includes a housing 210 that extends along the axis from a first end 212 to a second end 214.
  • a wall 216 of the housing 210 defines an interior passage 218 that extends the length of the housing.
  • a turbine 220, a compressor 230, and at least one combustor 240 are positioned within the passage 218 of the housing 210 and along the axis 202.
  • the compressor 230 includes a shaft or connecting member 232 that connects the compressor to the turbine 220 such that the connecting member and turbine rotate together.
  • the combustor 240 is positioned axially between the turbine 220 and the compressor 230.
  • the combustor 240 includes outer and inner tubes 242, 244 that are concentric to one another about a central axis 241 and secured to one another and the housing 210.
  • the central axis 241 of the combustor 240 may be coaxial with the axis 202 of the engine 202 or may be spaced from the axis of the engine (not shown).
  • the connecting member 232 extends through the inner tube 244 and a shaft seal 233 is provided between the connecting member and the inner tube to prevent fluid from passing between the connecting member and the inner tube directly into the turbine 220.
  • the space between the outer and inner tubes 242, 244 defines a fluid
  • the periphery of the outer tube 242 includes fluid directing structure 248 for directing fluid radially inward to the fluid passage 274. More specifically, the fluid directing structure 248 is configured to direct fluid to the fluid passage 274 in a direction that is offset from the central axis 241 of the combustor 240 and along a path that is angled relative to the normal of the inner surface (not shown) of the outer tube 242.
  • the periphery of the inner tube 244 includes fluid directing structure 252 for directing fluid from the interior 250 of the inner tube radially outward into the fluid passage 274. More specifically, the fluid directing strucnire 252 is wrdigured to direct fluid into the fluid passage 274 in a direction that is offset from the central axis 241 of the combustor 240 and along a path that is angled relative to the normal of the outer surface (not shown) of the inner tube 244.
  • the fluid directing structures 248, 252 may direct their respective fluid in the same general direction.
  • the fluid directing structure 248, 252 may include a series of openings with associated fins or guides for directing the fluid in the desired manner (Figs. 3 A-4D).
  • the jet engine 200 further includes one or more tubular fuel supply members 254 that extend into or are otherwise in direct fluid communication with the fluid passage 274 of the combustor 240 and extend radially outward from the passage, through the wall 216 of the housing 210, and to a fuel source (not shown) outside of the housing.
  • the fuel supply members 254 thereby deliver fuel directly to the fluid passage 274, as indicated generally by arrows Fl.
  • six fuel supply members 254 spaced radially equidistant from one another are illustrated in Figs. 1 -2B, it will be appreciated that any number of fuel supply members exhibiting any spacing
  • a ring-shaped wall 251 (see Fig. 2B) is secured to the end of the outer and inner tubes 242, 244 closer to the compressor 230 in order to seal one end of the fluid passage 274 in a fluid-tight manner.
  • the wall 251 is provided with openings 253 that receive ends of the fuel supply members 254 to establish the direct fluid path between the fuel supply members and the fluid passage 274.
  • Some of the compressed air exiting the compressor 230 flows directly into the interior 250 of the inner tube 244 as indicated generally by the arrows D3 and through the fluid directing structure 252 in the inner tube 244 into the fluid passage 274.
  • Some of the compressed air also flows to the peripheral annular space 277 between the outer tube 242 and the wall 216 of the housing 212, where it flows through the fluid directing structure 248 in the outer tube and into the fluid passage 274 as indicated generally by arrows D4.
  • a wall 255 secured to the end of the outer and inner tubes 242, 244 closer to the turbine 220 and between the outer tube and the wall 216 of the housing 210 prevents the compressed air D4 from passing into the turbine without first passing through the combustor 240.
  • the compressed air D3, D4 is mixed with fuel Fl that is injected into the combustor 240 via the fuel supply members 254. Since the ring-shaped wall 251 blocks the end of the fluid passage 274 adjacent to the compressor 230, the fuel Fl is directed by the fuel supply members 254 directly into the fluid passage 274.
  • the fluid directing structures 248, 252 of the combustor 240 only control the flow of compressed air D4, D3 into the fluid passage 274 such that the compressed air mixes with the fuel F 1 from the fuel supply members 254 within the fluid passage 274 in a desired manner. More specifically, as the peripheral air D4 passes through the fluid directing structure 248 in the outer tube 242 and into the fluid passage 274, the air mixes with the fuel Fl exiting the fuel supply members 254. Due to the configuration of the fluid directing structure 248, the compressed air D4 is imparted with a centrifugal force about the central axis 241 of the combustor 240 as it enters the fluid passage 274. The swirling air D4 mixes with the fuel Fl to create a swirling air/fuel mixture within the fluid passage 274 and about the central axis 241 of the combustor 240.
  • the compressed air D3 enters the interior 250 of the inner tube 244 and passes through the fuel directing structure 2S2 of the inner tube 244 and into the fluid passage 274, thereby imparting a centrifugal force upon the compressed air D3 about the central axis 241 of the combustor 240.
  • the swirling air D3 mixes with the fuel Fl to create an additional swirling air/fuel mixture within the fluid passage 274 and about the central axis 241 of the combustor 240.
  • the mixture formed from the fuel Fl and the compressed air D3 mixes with and becomes indistinguishable from the mixture formed from the fuel Fl and the compressed air D4 within the fluid passage 274.
  • the fluid directing structures 248, 252 extend around the entire periphery of the outer tube 242 and the inner tube 244, respectively, the collective air/fuel mixture within the fluid passage 274 is forced generally in a single direction, indicated by arrow R (Fig. 2B), that is transverse to the central axis 241 of the combustor 240. It will be appreciated that the fluid directing structures 248, 252 may direct the respective air/fuel mixtures in the same direction, e.g., clockwise relative to the central axis 241, within the fluid passage 274. Consequently, the air/fuel mixture within the fluid passage 274 undergoes a rotational, spiraling effect relative to the central axis 241 of the combustor 240 and within the fluid passage 274.
  • the rotating, spiraling air/fuel mixture is ignited by an ignition device (not shown) of any number of types well known in the art and positioned in any number of suitable locations to light the combustor 240.
  • the wall 251 may be provided with an opening (not shown) through which an igniter extends.
  • Flame proving means (not shown) may be positioned in any number of suitable locations to detect the presence of flame.
  • the combustion products from the ignited air/fuel mixture exit the combustor 240 rotating about the central axis 241 of the combustor 240 and the axis 202 of the jet engine 200 as indicated generally by arrows R2.
  • the combustion products of the air/fuel mixture exit the combustor 240 at elevated pressure and velocity and pass through the turbine 220, thereby imparting rotation upon the turbine as indicated generally by arrow R3.
  • the turbine 220 directs the combustion products out of the jet engine 200 in the direction indicated generally by arrows T to provide thrust to the aircraft. Since the connecting member 232 rotatably connects the turbine 220 to the compressor 230, the rotating turbine drives the compressor.
  • Each of the fluid directing structures 248, 252 may have any configuration suitable for imparting rotation to the compressed air D4, D3, respectively, to form an air/fuel mixture with the fuel F 1 and within the fluid passage 274 that swirls about the central axis 241 of the combustor 240 in accordance with the present invention.
  • Figs. 3A-3B illustrate one configuration of the fluid directing structure 252 of the inner tube 244 and those having ordinary skill will appreciate that the fluid directing structure 248 of the outer tube 242 may have a similar construction to the fluid directing structure 252.
  • the fluid directing structures 248 and 252 may be dissimilar (not shown). In any case, the fluid directing structure 248 is configured to direct fluid radially inward while the fluid directing structure 252 is configured to direct fluid radially outward.
  • the fluid directing structure 252 includes a plurality of openings 284 in the inner tube 244 for allowing the compressed air D3 to pass radially outward from the central passage 250 of the inner tube to the fluid passage 274.
  • Each of the openings 284 extends entirely through the inner tube 244 from an inner surface 282 to an outer surface 280.
  • Each opening 284 may have any shape, such as rectangular, square, circular, triangular, etc.
  • the openings 284 may all have the same shape or different shapes.
  • the openings 284 are aligned with one another along the periphery, i.e., around the circumference, of the inner tube 244 to form an endless loop.
  • One or more endless loops of openings 284 may be positioned adjacent to one another or spaced from one another along the length of the inner tube 244. Each loop may have any number of openings 284. The openings 284 in adjacent loops may be aligned with one another or may be offset from one another. The size, shape, configuration, and alignment of the openings 284 in the inner tube 244 is dictated by desired flow and performance characteristics of the compressed air D3 flowing through the openings.
  • openings 284 are illustrated as being arranged in a predetermined pattern along the inner tube 244, it will be appreciated that the openings may be randomly positioned along the inner tube (not shown).
  • Each opening 284 includes a corresponding fluid directing projection or guide 286 for directing the compressed air D3 passing through the associated opening radially outward into the fluid passage 274 and in a direction that is offset from the central axis 241 of the combustor 240, i.e., a direction that will not intersect the central axis.
  • the guides 286 are formed on or integrally attached to the inner surface 282 and/or the outer surface 280 (not shown) of the inner tube 244. Each guide 286 extends at an angle (shown in Fig. 3b) relative to the outer surface 280 of the inner tube 244.
  • the guides 286 may extend at the same angle or at different angles relative to the outer surface 280 of the inner tube 244.
  • Each guide 286 extends at an angle, indicated at a2, relative to an axis 287 extending normal to the outer surface 280 of the inner tube 244.
  • the fluid directing structure 248 on the outer tube 242 may be formed similar to the fluid directing structure 2S2 on the inner tube 244, those having ordinary skill in the art will appreciate that guides and openings associated with the fluid directing structure 248 (not shown) direct the compressed air D4 passing through the outer tube radially inward toward the central passage 274 and in a direction that is offset from the central axis 241 of the combustor 240. Similar to the fluid directing structure 252 on the inner tube 244, the guides of the fluid directing structure 248 on the outer tube 242 may be formed in or integrally attached to the inner surface and/or the outer surface of the outer tube (not shown).
  • the fluid directing structures 248, 252 direct the associated incoming compressed air D4, D3 in the same general direction such that the combined air/fuel mixture swirls within the fluid passage 274 around the central axis 241 of the combustor 240 in the same general direction.
  • Figs. 4A-D illustrate alternative configurations of the fluid directing structure 252 in the inner tube 244 in accordance with the present invention.
  • the fluid directing structure 252a-d directs the incoming compressed air D3 radially outward into the fluid passage 274 and in a direction that is 1) offset from the central axis 241 and 2) angled relative to the normal of the outer surface 280 of the inner tube 244 such that compressed air mixes with the fuel Fl to form an air/fuel mixture within the central passage 274 that exhibits a swirling, rotational path around the central axis while becoming radially layered relative to the central axis.
  • the openings in the fluid directing structure may be randomly positioned along the inner tube 244 or may be arranged in any predetermined pattern dictated by desired flow and performance criterion.
  • Figs. 4A-D illustrate alternative configurations of the fluid directing structure 252, 248 that may be formed on or integrally attached to the inner and/or outer surface of the respective tube 244, 242 in accordance with the present invention. More specifically, either of the fluid directing structures 248, 252 may exhibit any of the configurations shown in Figs. 4A-D.
  • the fluid directing structure 248 directs the incoming compressed air D4 radially inward into the fluid passage 274 and in a direction that is 1) offset from the central axis 241 and 2) angled relative to the normal of the inner surface of the outer tube 242 (not shown) such that the compressed air mixes with the fuel Fl to form an air/fuel mixture that exhibits a swirling, rotational path within the central passage 274 and around the central axis.
  • the fluid directing structure 252 directs the incoming compressed air D3 radially outward into the fluid passage 274 and in a direction that is 1 ) offset from the central axis 241 and 2) angled relative to the normal of the outer surface 280 of the inner tube 244 (not shown) such that compressed air mixes with the fuel F 1 to form an air/fuel mixture that exhibits a swirling, rotational path within the central passage 274 and around the central axis.
  • the openings in the fluid directing structure 248, 252 may be randomly positioned along the respective tube 242, 244 or may be arranged in any predetermined pattern dictated by desired flow and performance criterion.
  • the fluid directing structure 252a includes a plurality of guides 286a that define openings 284a in the inner tube 244a.
  • the guides 286a are arranged in a serics of rows that extend around the periphery of the inner tube 244a.
  • the annular rows are positioned next to one another along the length of the inner tube 244a.
  • the guides 286a of adjacent rows may be radially offset from one another or may be radially aligned with one another (not shown).
  • the guides 286a in each row may be similar or dissimilar to one another.
  • the guides 286a direct the compressed air D3 .
  • the inner tube 244b is formed as a series of steps that each includes a first member 283 and a second member 285 that extends substantially perpendicular to the first member to form an L-shaped step.
  • the second member 28S of each step includes a plurality of openings 284b for directing the compressed air D3 in a direction that is offset from the central axis 241 and angled relative to the axis (not shown) extending normal to the outer surface 280b of the inner tube 244b.
  • the openings 284b in each second member 285 direct the compressed air D3 across the first member 283 of the adjoining step to impart rotation to the compressed air and, thus, to the air/fuel mixture within the fluid passage 274 about the central axis 241.
  • the fluid directing structure 252c includes a plurality of openings 284c that extend from the inner surface 282c of the inner tube 244c to the outer surface 280c.
  • the openings 284c extend through the inner tube 244c at an angle relative to the axis 287c extending normal to the outer surface 280c of the inner tube 244c and through the central axis 241 of the combustor 240.
  • the openings 284c in the inner tube 244c direct the compressed air D3 and, thus, the air/fuel mixture within the fluid passage 274 in a direction that is offset from the central axis 241 and at an angle relative to the axis 287c in order to impart rotation to the air/fuel mixture within the fluid passage about the central axis.
  • the fluid directing structure 252d is formed by a series of arcuate, overlapping plates 330 that cooperate to form the inner tube 244d.
  • Each plate 330 has a corrugated profile that includes peaks 332 and valleys 334.
  • the plates 330 are longitudinally and radially offset from one another such that that peaks 332 of one plate 330 are spaced between the peaks of adjacent plates. In this configuration, the peaks 332 and valleys 334 of the plates create passages 336 through which the compressed air D3 is directed.
  • Each plate 330 directs the compressed air D3 in a direction that extends substantially parallel to the adjoining arcuate plate to impart rotation to the compressed air and, thus, to the air/fuel mixture within the fluid passage 274 about the central axis 241.
  • the air/fuel mixture within the fluid passage 274 is thereby directed in a direction that is offset from the central axis 241 of the combustor 240 and angled relative to the axis (not shown) extending normal to the plates 330.
  • Figs. 5-6A illustrate a jet engine 200a in accordance with another embodiment of the present invention.
  • Features in Figs. 5-6A that are identical to features in Figs. 1- 2B have the same reference number as Figs. 1-2B, whereas features in Figs. 5-6A that are not similar to features in Figs. 1-2B are given the suffix "a".
  • Figs. 5-6A illustrate a jet engine 200a similar to the jet engine 200 of Figs. 1 -2B.
  • the fuel being delivered via the fuel pipe 254a is partially mixed with air prior to being injected into the region 274.
  • the partially pre-mixed fuel is indicated by the reference character F3 and, as seen best in Fig.
  • the fuel pipe 254a passes through a pre-mix chamber 254'.
  • the pre-mix chamber 254' receives compressor air indicated by the reference character D5 through a port (not specifically shown) formed in the pre-mix chamber 254'.
  • Fuel passing through the chamber mixes with the incoming air stream (D5) and is injected to the region 274 where it is mixed with additional air D4, D3 delivered through ports 252, 248 formed in the members 244, 242, respectively (see also Fig. 2B).
  • the jet engine burner shown in Fig. 6A operates essentially similar to the burner shown in Fig. 2 A, except that the fuel is pre-mixed with some air prior to being injected into the region 274.
  • the fuel and air movement patterns shown in Fig. 2B are equally applicable to the burner shown in Fig. 6 A.
  • the fuel delivered by the fuel supply members 254a is partially pre-mixed with the incoming compressed air D5 before being discharged into the chamber 274.
  • This partial fuel mixture is further mixed with compressed air D3 and D4 which is injected through the respective fluid directing structure 252 and 248 and into the fluid passage/combustion chamber 274' where the fully mixed fuel charge is ignited and burned.
  • the fluid directing structure 252 allows the air D3 within the passage 250 to be directed radially outward into the fluid passage 274, and the fluid directing structure 248 allows the air D4 in the region 277 outside of the outer tube 242 to be directed radially inward into the fluid passage 274.
  • Either or both of the fluid directing structures 248, 252 may have any of the configurations illustrated in Figs. 3A-4D.
  • the compressed air D3, D4 mixes with the partial fuel mixture F3 from the fuel supply members 254a to form an air/fuel mixture within the fluid passage 274 that swirls around the axis 241 of the combustor 240a. Due to the configuration of the fluid directing structure 248, the compressed air D4 is imparted with a centrifugal force about the axis 241 of the combustor 240a as it passes into the fluid passage 274.
  • the compressed air D3 enters the interior 250 of the inner tube 244 and then through the directing structure 252 of the inner tube 244 and into the fluid passage 274, thereby imparting a centrifugal force upon the air/fuel mixture about the axis 241 of the combustor 240a.
  • a mixture of air and fuel is formed in the fluid passage and imparted with a centrifugal force that causes the air/fuel mixture within the fluid passage 274 to rotate or spiral around the central axis of the combustor, thus improving and stabilizing combustion.
  • Figs. 7-8 illustrate a jet engine 200b in accordance with another embodiment of the present invention.
  • Features in Figs. 7-8 that are identical to features in Figs. 1-2B or Figs. 5-6A have the same reference number as Figs. 1-2B or Figs. 5-6A, whereas features in Figs. 7-8 that are not similar to features in Figs. 1-2B are given the suffix "b".
  • a wall 251 b is secured to the end of the combustor 240b closer to the compressor 230 and a wall 255b is secured to the end of the combustor closer to the turbine 220.
  • the fuel F4 is injected upstream from the combustor and is completely mixed with compressed air D4' before entering the combustor 240b.
  • the jet engine 200b of Figs. 7-8 includes a fluid mixing element 290 secured to the housing 210 for pre-mixing the compressed air D4' and fuel F4 exiting the fuel supply members 254b such that the air and fuel is completely mixed prior to entering the combustor 240b.
  • the fluid mixing element 290 is positioned along the axis 202 of the jet engine 200b between the fuel supply members 254b and the combustor 240b and includes an outer element 292 and an inner element 294 positioned concentric to one another and the connecting member 232.
  • the outer element 292 is ring-shaped and has a generally frustoconical configuration that tapers radially inward in a direction extending towards the combustor 240b, i.e., leftward as viewed in Fig. 8.
  • the inner element 294 is positioned in the interior of the outer element 292 and is secured to or integrally formed with the outer element.
  • the compressor/turbine connecting member 232 extends through an opening indicated generally by the reference character 294a in the inner element 294.
  • An annular gap 296 extends between the inner element 294 and the outer element 292 and tapers inwardly in a direction extending towards the combustor 240b, i.e., the cross-sectional area of the gap along the axis 202 decreases in the direction towards the combustor.
  • the fluid mixing element 290 is configured such that the compressed air D4' from the compressor and the fuel F4 exiting the fuel supply members 254b must pass through the gap 296 in the mixing element in order to reach the combustor 240b.
  • the compressed air D4' and fuel F4 become mixed together as the air and fuel travel through the fluid mixing element
  • the air D4' and fuel F4 exit the fluid mixing element 290 as a fully pre-mixed mixture, indicated generally as M in Fig. 8.
  • M the fluid mixing element 290 is illustrated as having a particular construction, those having ordinary skill will appreciate that any structure or structures may be used that are configured to mix the compressed air D4' and fuel F4 to form a fully pre-mixed mixture M that enters the combustor 240b to be ignited.
  • the mixture M enters the combustor 240b along two different pathways. Some of the mixture M flows to the region 277, i.e., the exterior of the combustor 240b between the wall 216 of the housing 210 and the outer tube 242, where it is directed radially inward by the fluid directing structure 248 of the outer tube 242 into the fluid passage 274. The remainder of the mixture M flows into the interior 250 of the inner tube 244 where it is directed radially outward by the fluid directing structure 252 of the inner tube into the fluid passage 274.
  • the fluid directing structures 248, 252 cause the collective mixture M to swirl within the fluid passage 274 around the axis 241 of the combustor 240b in a manner similar to that illustrated in Fig. 2B.
  • the mixture M is then ignited within the fluid passage 274 by an ignition source (not shown) and the combustion products of the ignited mixture are expelled from the combustor 240b towards the turbine 220 in the manner indicated generally by arrows R2 in order to drive the turbine in the manner described.
  • Figs. 9-11 illustrate a jet engine 200c in accordance with another aspect of the present invention.
  • a plurality of combustors 240c is arranged about the central axis 202 of the jet engine.
  • Each of the combustors 240c may constitute the non-pre-mixed combustor 240 of Figs. 1-2B, the partially pre-mixed combustor 240a of Figs. 5-6 ⁇ or the fully pre-mixed combustor 240b of Figs. 7-8 or modifications thereof.
  • Features in Figs. 9-11 that are identical to features in Figs. 1-8 have the same reference number as Figs. 1 -8, whereas features in Figs. 9-11 that are similar to features in Figs. 1-8 are given the suffix "c".
  • the compressor 230 and the turbine 220 are positioned within the housing 210 on opposing sides of the combustors 240c.
  • the combustors 240c are preferably axially aligned with one another and are radially spaced about the axis 202 of the jet engine 200c (Fig. 9). Although five combustors 240c are illustrated in Figs. 9-11, it will be appreciated that more or fewer combustors may be provided in accordance with the present invention. Furthermore, the combustors 240c may be symmetrically or asymmetrically spaced about the central axis 202.
  • the combustors 240c may be symmetrically or asymmetrically spaced about the central axis 202.
  • a wall 270 is provided between the wall 212 of the housing 210 and the combustors 240c and between the combustors to ensure that fluid only flows into the combustors, i.e., not around or between the combustors and the wall of the housing.
  • Another wall 272 is also preferably provided to prevent air or fuel/air from bypassing the combustors.
  • the walls 270, 272 may also serve as mounting plates or supports for the combustors 240c.
  • the combustors 240c are different from the combustors 240, 240a, 240b in that no inner tube is used.
  • the outer tube 242' of the combustor has fluid directing structure 248 such that the mixture of air and fuel is directed from a fluid passage 277' radially inward through the fluid directing structure into the interior 274'.
  • each combustor 240c includes a solid outer wall 297 that has a continuous surface such that no fluid passes radially through it
  • a cap 251c is provided on each combustor 240c to fluidly seal the upstream end of the tube 242 closer to the turbine 200 such that air and/or the fuel/air mixture cannot axially enter the passage 274' of the combustor 240c, i.e., the air and/or fuel mixture must pass radially inward through the fluid directing structure 248' and into the interior passage 274'.
  • the downstream end of the annular passage 277* is sealed by a cap 257a which ensures that all the air (or fuel-air mixture) travels into the combustion passage 274 * .
  • Air exiting the compressor 230 is distributed amongst the combustors 240c.
  • the air is mixed with fuel delivered by the fuel pipe 254c and is ultimately swirled and burned in the inner combustion chamber 274'.
  • Fig. 10 Several methods and apparatus for injecting fuel into the burner 240c are illustrated in Fig. 10.
  • a fuel pipe 254c is shown in solid and, in the solid configuration, fuel is injected upstream of the combustor 240c where it is fully mixed with air delivered by the compressor 230 as described in connection with Figs. 7, 8A and 8B.
  • This fully mixed fuel/air charge then enters the region 277' and travels into the combustion passage 274' via ports 248 formed in the tubular member 242'.
  • the ports are arranged to cause rotation of the fuel/air mixture in the combustion passage 274'.
  • each combustor 240c utilizes the fuel/air delivery system described in connection with Figs. 5 and 6A.
  • a fuel pipe 254c' includes a pre- mix chamber 254".
  • the fuel being delivered by the fuel pipe 254c' is partially mixed with air received by the pre-mix chamber 254" from the compressor 230.
  • This partial fuel mixture is injected into the chamber 274' through the cap 25 lc where it fully mixed with compressor air D6 that enters the chamber 274' via the passage 277' and then the ports 248 formed in the tubular member 242'.
  • the combustors 240c utilize the fuel/air delivery system described in connection with Figs. 1 and 2A.
  • the fuel is injected directly into the combustion passage 274' via the fuel pipe 254c, the downstream end of which extends thought the cap 25 lc.
  • the injected fuel is mixed with the swirling air delivered through the tubular member 242'.
  • an igniter within the interior 274' of the tube member 242' of each combustor 240c ignites the swirling air/fuel mixtures.
  • the swirling combustion products collectively exit the combustors 240c and pass through the turbine 220, causing rotation of the turbine and expulsion of the
  • the combustor of the present invention for use in a jet engine is advantageous over conventional combustors or burners for several reasons.
  • the combustor of the present invention forces additional heat transfer by convection and radiation from the high velocity flame envelope overlaying and intermixing with the incoming air/fuel mixture.
  • the incoming air/fuel mixture is pre-heated while the flame zone is being cooled, which
  • Radicals are also forced into the incoming reactant stream by the overlaying and intermixing flame envelope.
  • the presence of radicals in a mixture of reactants lowers the ignition temperature and allows the fuel to burn at lower than normal temperature. It also helps to significantly increase flame speed, which shortens the reaction time, thereby additionally reducing NO x formation while significantly improving flame stability/flame retention.
  • the improved stability and flame retention reduces the chances of flame out.
  • the combustor of the present invention Due to the exceptional flame retention/stability of the combustor of the present invention, it is capable of running at very high combustion loadings. High loadings allow the burner to run in a stable "lifted flame” mode i.e., the flame is spaced from the combustor surfaces. Lifting of the flame in this manner is desirable in that the combustor surfaces are not directly heated, thereby maintaining the surfaces at a lower temperature and lengthening the usable life of the combustor. A high combustion loading also allows the use of a smaller, space saving, and less costly combustor for a given application. Furthermore, the combustor of the present invention, due to the exceptional flame retention as discussed above, is also capable of operating cleanly (low CO) at very high levels of excess air, which produces NOx levels well below those achievable with conventional combustors.
  • any of the combustors described above may incorporate a "variable volume" combustion chamber, e.g., fluid passage, by configuring the wall 25 lc (shown in Fig. 9) secured to the inner and outer tubes to be movable along the axis of the jet engine.
  • a "variable volume" combustion chamber e.g., fluid passage
  • the wall 25 lc shown in Fig. 9
  • Such a construction would allow for optimized combustion performance by matching the combustion chamber volume to the power output required.
  • the invention has been described in detail in connection with a jet engine application. Those skilled in the art will recognize that the principles of this invention may be applied to burners used in heating appliances such as hot water tanks, furnaces and boilers. Those skilled in the art will recognize that the disclosed burner configurations can be adapted for use in the identified heating applications. For some applications, the burner would be configured as a power burner in which a blower or the suitable device would force air into the burner where it would be mixed with the suitable liquid fuel such as fuel oil or a gaseous fuel such as natural gas or propane.
  • suitable liquid fuel such as fuel oil or a gaseous fuel such as natural gas or propane.

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  • 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 concerne un procédé de combustion et une chambre de combustion destinés à être utilisés dans un moteur à réaction, le moteur à réaction ayant une partie compresseur et une partie turbine. La chambre de combustion comprend un tube externe ayant un axe central qui s'étend longitudinalement entre la partie compresseur et la partie turbine et est positionnée pour recevoir de l'air évacué par la partie compresseur. Un tube interne est positionné à l'intérieur du tube externe et comprend une surface externe associée espacée de la surface interne du tube externe, définissant ainsi un espace de combustion. Le tube externe et le tube interne comprennent une structure de direction de fluide destinée à communiquer à l'espace de combustion au moins une partie de l'air évacué par la partie compresseur. La structure de direction de fluide dirige de l'air dans l'espace de combustion dans une direction décalée de l'axe central, provoquant ainsi une rotation ou un tourbillonnement de l'air autour de l'axe central.
PCT/US2012/050349 2011-08-11 2012-08-10 Chambre de combustion WO2013023147A1 (fr)

Priority Applications (4)

Application Number Priority Date Filing Date Title
EP12822757.6A EP2742292A4 (fr) 2011-08-11 2012-08-10 Chambre de combustion
CA2844693A CA2844693A1 (fr) 2011-08-11 2012-08-10 Chambre de combustion
CN201280050137.7A CN103998867A (zh) 2011-08-11 2012-08-10 燃烧室
US14/238,067 US20140190178A1 (en) 2011-08-11 2012-08-10 Combustor

Applications Claiming Priority (2)

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US201161522412P 2011-08-11 2011-08-11
US61/522,412 2011-08-11

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WO2013023147A1 true WO2013023147A1 (fr) 2013-02-14

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CN (1) CN103998867A (fr)
CA (1) CA2844693A1 (fr)
WO (1) WO2013023147A1 (fr)

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EP2778530A1 (fr) * 2013-03-12 2014-09-17 Pratt & Whitney Canada Corp. Chambre de combustion pour moteur à turbine à gaz
US9228747B2 (en) 2013-03-12 2016-01-05 Pratt & Whitney Canada Corp. Combustor for gas turbine engine
US9366187B2 (en) 2013-03-12 2016-06-14 Pratt & Whitney Canada Corp. Slinger combustor
US9541292B2 (en) 2013-03-12 2017-01-10 Pratt & Whitney Canada Corp. Combustor for gas turbine engine
US9958161B2 (en) 2013-03-12 2018-05-01 Pratt & Whitney Canada Corp. Combustor for gas turbine engine
CN110440290A (zh) * 2018-05-02 2019-11-12 中国联合重型燃气轮机技术有限公司 用于燃气轮机的微混合喷嘴

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US10634354B2 (en) 2011-08-11 2020-04-28 Beckett Gas, Inc. Combustor
CN104373962B (zh) * 2014-10-28 2016-08-24 北京华清燃气轮机与煤气化联合循环工程技术有限公司 一种燃气轮机燃烧室叶片进气旋流喷嘴
EP4283197A3 (fr) * 2016-11-22 2024-02-14 Beckett Thermal Solutions Chambre de combustion
KR102583222B1 (ko) 2022-01-06 2023-09-25 두산에너빌리티 주식회사 연소기용 노즐, 연소기 및 이를 포함하는 가스 터빈

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Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2778530A1 (fr) * 2013-03-12 2014-09-17 Pratt & Whitney Canada Corp. Chambre de combustion pour moteur à turbine à gaz
US9127843B2 (en) 2013-03-12 2015-09-08 Pratt & Whitney Canada Corp. Combustor for gas turbine engine
US20150338102A1 (en) * 2013-03-12 2015-11-26 Pratt & Whitney Canada Corp. Combustor for gas turbine engine
US9228747B2 (en) 2013-03-12 2016-01-05 Pratt & Whitney Canada Corp. Combustor for gas turbine engine
US9366187B2 (en) 2013-03-12 2016-06-14 Pratt & Whitney Canada Corp. Slinger combustor
US9541292B2 (en) 2013-03-12 2017-01-10 Pratt & Whitney Canada Corp. Combustor for gas turbine engine
US9958161B2 (en) 2013-03-12 2018-05-01 Pratt & Whitney Canada Corp. Combustor for gas turbine engine
US10378774B2 (en) 2013-03-12 2019-08-13 Pratt & Whitney Canada Corp. Annular combustor with scoop ring for gas turbine engine
US10788209B2 (en) 2013-03-12 2020-09-29 Pratt & Whitney Canada Corp. Combustor for gas turbine engine
US10955140B2 (en) 2013-03-12 2021-03-23 Pratt & Whitney Canada Corp. Combustor for gas turbine engine
CN110440290A (zh) * 2018-05-02 2019-11-12 中国联合重型燃气轮机技术有限公司 用于燃气轮机的微混合喷嘴
CN110440290B (zh) * 2018-05-02 2024-03-29 中国联合重型燃气轮机技术有限公司 用于燃气轮机的微混合喷嘴

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EP2742292A4 (fr) 2015-08-12
EP2742292A1 (fr) 2014-06-18
CA2844693A1 (fr) 2013-02-14
US20140190178A1 (en) 2014-07-10
CN103998867A (zh) 2014-08-20

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