US2781638A - Combustion apparatus and liquid fuel discharge apparatus adapted for use therewith - Google Patents

Combustion apparatus and liquid fuel discharge apparatus adapted for use therewith Download PDF

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Publication number
US2781638A
US2781638A US371028A US37102853A US2781638A US 2781638 A US2781638 A US 2781638A US 371028 A US371028 A US 371028A US 37102853 A US37102853 A US 37102853A US 2781638 A US2781638 A US 2781638A
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United States
Prior art keywords
fuel
main
discharge
spill
pilot
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US371028A
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English (en)
Inventor
Fletcher Walter George
Ashwood Peter Frederick
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Power Jets Research and Development Ltd
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Power Jets Research and Development Ltd
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    • 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
    • F23R3/34—Feeding into different combustion zones
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/24—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space by pressurisation of the fuel before a nozzle through which it is sprayed by a substantial pressure reduction into a space
    • F23D11/26—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space by pressurisation of the fuel before a nozzle through which it is sprayed by a substantial pressure reduction into a space with provision for varying the rate at which the fuel is sprayed
    • F23D11/28—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space by pressurisation of the fuel before a nozzle through which it is sprayed by a substantial pressure reduction into a space with provision for varying the rate at which the fuel is sprayed with flow-back of fuel at the burner, e.g. using by-pass

Definitions

  • This invention relates to combustion apparatus and to liquid discharge apparatus adapted for use therewith and its primary odbject, stated in general terms, is the provision of a combustion apparatus and liquid fuel burner, which will offer the possibility of eifective and efiicient combustion over a wide range of operating conditions. 'Whilst, as will be seen after consideration of its details, the liquid discharge apparatus of the invention.
  • the invention is primarily concerned and is at present conceived to have its maximum utility in connection with liquid fuel combustion apparatus in which special problems arise due to the necessity for supporting combustion by means of a fast moving, air current involving a large mass flow as for example, in gas turbine or/and jet propulsion power units, the description fast moving beingtused here to indicate that the -mean speed of the combustion supporting air current in its general direction of flow past a combustionzone, calculated from the ratio air volume passing in unit time/cross sectional area of flow path, is substantially higher than the speed of flame propagation in the fuel/air mixture concerned.
  • the speed of flame propagation- is considered as being of theorder of one foot per second at atmospheric temperature; the invention is'especiauy applicable to combustion apparatus for gas turbine or/and jet propulsion power units in which the air current in its general direction of flow past acotnbustion zone, calculated'on the basis indicated, might be of an'ordei' as low as 10'or as high as '300 feet per second 'oreven more, de pendingonthedesign.
  • the-latter coming into operation automatically, but only when the fuel delivery requirements rise above a predetermined minimum and the pilot discharge alone operating below that minimum, and in which the introduction of air from the main sup ply to the main pilot discharge respectively for their combustion is controlled in such a way that the actual air supply to the latter remains substantially constant, or at least varies only over a relatively small range as compared with the actual air supply to the former, which is allowed to be influenced to a major extent by variations in the main air supply.
  • a liquid discharge apparatus in whichxthere is a mainliquid discharge device of the spill type as defined below and a pilot liquid discharge device whichis supplied and maintained from the spill of liquid from the main liquid discharge device.
  • the expression spill type is'used here to indicate the known arrangement of liquid discharge device in which the discharge takes place from a chamber in which the liquid is caused to swirl and which has a spill or return port for returning liquid to source and a discharge port or atomising jet both on the axis of swirl, the output from the discharge port or atomising jet being controlled by varying the rate of spill and the discharge ceasing entirely at a given high rate of spill.
  • the structural relationship of the main and pilot discharge devices is immaterial and they can be suitably-disposed and connected by appropriate liquid ducts in accordance with the requirements of any particular case. According to a further feature of the invention, however, the two devices are combined in one structural unit. It will be seen that with an arrangement of this character, by suitably relating the flow capacities of the main discharge port and the spill or return line, it can be arranged that after discharge from the main port has ceased due to reduction of the spill rate the pilot dis-. charge will continue to take place.
  • Aliquid discharge apparatus in accordance with the invention has the advantage that it combines with the extremely good atomisation for all outputs characteristic of the spill type of dis charge device, a pilot discharge capable of dealing.
  • the device can therefore be used to advantage to provide a pilot discharge of fuel at low demands and a main discharge ruption of supply when the main discharge commences.
  • Figure 1 is a sectional elevation of a liquid discharge device.
  • Figure 2 is a sectional elevation of a combustion apparatus with a liquid discharge device as shown in Figure 1. 1
  • Figure 3 is a diagrammatic layout of a fuel systemv and combustion system of a compressor gas-turbine unit for: combustion apparatus and liquid discharge device as;
  • the cap 14 has a tubular extension 16 of less diameter than the body into which it extends.
  • the cap 14 is retained in position by a headed plug 17 which is passed through a hole 18 in the dividing partition 13 from the chamber 12 and threaded into the bore 1.9 of the extension 16, this plug 17 axially filling the bore 19 of the main dis charge cap 14 except for a main discharge swirl chamber 20 containing the main discharge port 15, but having an axial passage 21 communicating with the compartmcnt 12 of the body it
  • the main discharge swirl chamber 29, which is of circular section coaxial with but of larger diameter than the discharge port and the axial passage or spill way 21 to the other compartment 12 has tangential inlets 22 communicating with the annular chamber 11 between the cap 14 and the body 10, to which space the supply is connected by a pipe 23. The fuel on entering the main discharge chamber through the tangential inlets 22 will be rapidly swirled therein.
  • the second compartment or chamber 12 of the body 10 is connected to a spill return or pipe 24 in which is a controllable valve 25 to vary the flow resistance;
  • the axial passage 21 through which the discharge chamber 20 of the main delivery port 15 communicates with the second compartment 12 thus constitutes a spill passage from the main discharge swirl chamber 20, this spill passage being of a diameter intermediate between that of the chamber 20 and its discharge port 15 so that according as the resistance in the spill line is raised or lowered, so the discharge from the main port 15 will be brought into operation or cut out.
  • a pilot discharge port 26 is formed in a screwed plug 27 threading into the chamber 12 of the body 10 at the end remote from the main discharge port 15.
  • the plug 27 is provided with a swirl chamber 28 co-axial with and of larger diameter than the discharge port 26 which is in communication with the chamber or spill compartment 12 of the body 10 through tangential inlets 29 communieating with passages 30 formed between the plug 27 and the body 10.
  • liquid discharge apparatus described above is admirably suited to the requirements of a combustion apparatus in accordance with the first aspect of the invention one form of which is shown by way of example in Figure 2; in that connection, the invention contemplates in general an arrangement in which the pilot discharge port 26 is placed upstream of the main discharge port 15 with reference to the direction of fiow of combustion supporting air, and in the case of the constructional example of discharge apparatus described, the main discharge would be directed downstream.
  • the pilot discharge port 26 would be screened from the main air flow by means of a perforated conical bafile 31 in a main outer air casing 32 allowing only a restricted air entry through air inlet holes 33 to ensure burning of the pilot fuel discharge under relatively constant conditions.
  • the conical baffie 31 may also be extended in the downstream direction within the outer casing 32 to form a flame tube 34 enclosing the main discharge of fuel from the port 15 for combustion thereof andlextending for a substantial distance downstream thereof, the main airflow passing around the flame tube.
  • the flame tube 34 should be enclosed by the outer casing. 32 which constitutes the principal air duct of the combustion apparatus; and in this connection it may be noted that when the pilot discharge port 26 is directed upstream, the baffle may incorporate the features of co-pending patent application No. 609,532,
  • the invention as applied to gas turbines is shown dia- 15 grammatically in Figure 3 together with a spill controlled fuel system which is essential to that type of combustion apparatus.
  • a main fuel pump 36 of substantially positive displacement type is driven from a compressor-gas turbine unit 37. it draws fuel through a suction pipe 30 38 from a fuel tank 39 and delivers fuel by the main delivery pipe 40 .through a high pressure filter 41 through a manually operated stop cock 42, a dump valve 43 and a dump valve 44, manifold pipes 45 and 46 and pipes 23 to starting spill burners 15 and main spill burners 1 in flame tubes 34 in air casings 32.
  • the fuel is spilled back through individual spill ways 21 in the burners (see Figure 1) through spill or return pipe 24 to spill manifolds 47 and 48 to return pipe 49, non-return valves 50 and 51, pipe 52, throttle valve 53 40 and return pipe 54 to fuel tank 39.
  • the throttle valve 53 is a manually controlled valve having a barometrically controlled relief valve to control the flow in accordance with ambient barometric pressure to obviate the adjust merit of the throttle valve by the pilot to maintain con- 45 slant turbine speed due to change in altitude or barometric pressure' at constant altitude as described in copending patent application No. 597,810 now U. S. Patent No. 2,669,245.
  • a supplementary pump cir- 50 cuit comprising a feed branch 55, a delivery branch 56 with a non-return valve 57, a pump 58 driven by the compressor-gas turbine starter motor 59.
  • a pipe 60 having a non-return valve 61 is arranged to lead fuel from a point between the filter and stop cock 42 back to the fuel tank 39 as the fuel pump 36 is selected and adjusted to deliver fuel at a higher rate than the turbine demands at any speed.
  • a centrifugal speed 60 controlling a governor valve 62 operating in accordance to the speed of the compressor gas-turbine 37 is arranged in a pipe 63 leading from the pipe 52 to the pipe 60.
  • the dump valves 43 and 44 which are change-over pressure operated valves operated by the fuel pressure are provided with drain connections 64 and 65 respectively joining common drain 66 leading to the fuel tank 39 to enable supply manifolds 45 and 46 to be drained when the'system is shut down.
  • the dump valves 43 and 44 are also provided with spill connections 67 and 68 70 respectively to connect the spill manifolds 47 and 48 to drain when the fuel supply is shut down.
  • dump valve 44 opening at a slightly higher pressure than dump valve.43.
  • dump valve 43 opens it admits fuel to the burners 15 fed by manifold 45 and admits fuel to dumpvalve 44.
  • dump valve 44 opens admitting fuel to main burners 1 fed by manifold 46.
  • the dump valves 43 and 44 are arranged in this manner toenable the starting burners fed by manifold 45 to be set in operation first in conjunction with spark ignition to start the compressor gas turbine unit 37.
  • the function of the non-return va lve 50 is to prevent fuelentering the main bur'ner'sli byway of manifold 48 when the starting burners 15 begin to operate.
  • the fuel flows by pipe 40 to the valves 43 and thence to the burners 15 when fuel pressure is suflicient to operate dump valve 43.
  • dump valve 43 opens and fuel commences to issue from the burners 15 igniters operate to start combustion in the starter burners 15.
  • the compressor gas turbine unit 37 then begins to accelerate and the pump 36 begins to operate and quickly raises the pressure in the pipe 40.
  • the non-return valve 57 closes and the starter motor is stopped.
  • the increased pressure in the pipe 40 also enables the dump valve 44 to open and supply fuel to the main burners 1 which are ignited and the compressor-gas turbine unit is running under its own power.
  • the dump valves 43 and 44 close cutting off the fuel supply to the burners and opening the burners 15 and 1, supply manifolds 45 and 46 and spill return manifolds 47 and 48 to drain. Any air pressure in the flame tubes 34 and air casings 32 to which the burners 15 and 1 are exposed tends to flow back through the burners 15 and 1 and out through the valves 43 and 44 to the fuel tank 39, preventing dribbling of the burners and emptying of the manifold pipes 45, 46, 47 and 48, which is found to be good practice.
  • combustion apparatus designed in accordance with the invention has been found to give satisfactory operation with good elficiency at weak mixtures and over a wide range of air/fuel ratios. For example, an efiiciency of 65% at a mixture strength of 700:1 has been obtained with a weak flame extinction limit as high as 900:1. It has also been found that the pressure loss can be kept very low and that a combustion can be produced whose operation is very stable and in which it is exceedingly diflicult to extinguish the flame by violent alterations of the fuel flow.
  • V Combustionapparatus for'burning a variable quan ti y of liquid fuel infa high-velocity variable air stream l flHP t g "bmbi tion a a 't b f t p ss e of *theairstream,-open"at its downstream end, a fuel injector lying along the stream within said tube, in the neighborhood of the upstream end of the tube, which injector has a continuously-operating pilot nozzle in its upstream end and a main nozzle in its downstream end, a source of supply of fuel to said injector feeding both said nozzles, control means for varying the rate of discharge of fuel from the said source through said main nozzle without appreciably affecting the discharge of fuel from the same source through said pilot nozzle, and a closure element at the upstream end of said flame tube finely perforated to admit to the region of the discharge from the
  • main and pilot injectors are constituted by a main and a pilot nozzle at the downstream and upstream ends respectively ofan injector unit lying along the air stream, the main nozzle discharging downstream and the pilot nozzle discharging continuously upstream from a spillway extending upstream from said main nozzle.
  • a liquid fuel discharge apparatus for producing a main fuel jet which can be varied over a wide range, and a continuously operating pilot jet from the same fuel supply, not appreciably 'afiected by the variation of the main jet, comprising a fuel discharge device, a fuel circulating system therethrough constituted by a supply connection thereto, and a spill return line therefrom, and means in said circulating system for causing the flow in said spill return line to differ variably from that in said supply connection, said fuel discharge device having a main nozzle of the spill type at one end, fed by said supply connection, a spillway extending from said main nozzle to said spill return line, and a pilot nozzlecat the other end of the device fed from said spillway.
  • said discharge device consists of a body enclosing a main swirl chamber formed on the axis of the body at one end thereof, from which chamber the main nozzle discharges axially, a tangential inlet to said chamber with which said supply connection is in communication, a co-axial pilot swirl chamber at the other end of the body from which chamber the pilot nozzle discharges, an intermediate space with which said return line is in communication, a spillway extending axially from the rear of said main whirl chamber to said intermediate space and a tangential inlet to said pilot swirl chamber in communication with said intermediate space.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
US371028A 1947-05-23 1953-07-29 Combustion apparatus and liquid fuel discharge apparatus adapted for use therewith Expired - Lifetime US2781638A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB13871/47A GB647344A (en) 1947-05-23 1947-05-23 Improvements in or relating to combustion apparatus

Publications (1)

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US2781638A true US2781638A (en) 1957-02-19

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US371028A Expired - Lifetime US2781638A (en) 1947-05-23 1953-07-29 Combustion apparatus and liquid fuel discharge apparatus adapted for use therewith

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US (1) US2781638A (US07534539-20090519-C00280.png)
BE (1) BE482650A (US07534539-20090519-C00280.png)
CH (1) CH270943A (US07534539-20090519-C00280.png)
FR (1) FR971755A (US07534539-20090519-C00280.png)
GB (1) GB647344A (US07534539-20090519-C00280.png)
NL (1) NL82287C (US07534539-20090519-C00280.png)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2944398A (en) * 1954-10-20 1960-07-12 Lockheed Aircraft Corp Combustion chamber for jet propulsion motors
US2951341A (en) * 1956-09-19 1960-09-06 Westinghouse Electric Corp Fuel injection system for an aircraft engine
US2974487A (en) * 1957-10-19 1961-03-14 Bristol Siddeley Engines Ltd Combustion system for a gas turbine engine
US4193260A (en) * 1976-09-04 1980-03-18 Rolls-Royce Limited Combustion apparatus
US4337616A (en) * 1980-04-14 1982-07-06 General Motors Corporation Fuel air ratio controlled fuel splitter
US5187936A (en) * 1990-10-17 1993-02-23 General Electric Company Continuous flow fuel circulation system
US20090111063A1 (en) * 2007-10-29 2009-04-30 General Electric Company Lean premixed, radial inflow, multi-annular staged nozzle, can-annular, dual-fuel combustor

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2944398A (en) * 1954-10-20 1960-07-12 Lockheed Aircraft Corp Combustion chamber for jet propulsion motors
US2951341A (en) * 1956-09-19 1960-09-06 Westinghouse Electric Corp Fuel injection system for an aircraft engine
US2974487A (en) * 1957-10-19 1961-03-14 Bristol Siddeley Engines Ltd Combustion system for a gas turbine engine
US4193260A (en) * 1976-09-04 1980-03-18 Rolls-Royce Limited Combustion apparatus
US4337616A (en) * 1980-04-14 1982-07-06 General Motors Corporation Fuel air ratio controlled fuel splitter
US5187936A (en) * 1990-10-17 1993-02-23 General Electric Company Continuous flow fuel circulation system
US20090111063A1 (en) * 2007-10-29 2009-04-30 General Electric Company Lean premixed, radial inflow, multi-annular staged nozzle, can-annular, dual-fuel combustor

Also Published As

Publication number Publication date
BE482650A (US07534539-20090519-C00280.png)
FR971755A (US07534539-20090519-C00280.png) 1951-01-22
GB647344A (en) 1950-12-13
NL82287C (US07534539-20090519-C00280.png)
CH270943A (de) 1950-09-30

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