US3626444A - Improvements in liquid fuel vaporizing combustion systems - Google Patents

Improvements in liquid fuel vaporizing combustion systems Download PDF

Info

Publication number
US3626444A
US3626444A US872605A US3626444DA US3626444A US 3626444 A US3626444 A US 3626444A US 872605 A US872605 A US 872605A US 3626444D A US3626444D A US 3626444DA US 3626444 A US3626444 A US 3626444A
Authority
US
United States
Prior art keywords
shank
combustion
tubular
arms
combustion chamber
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.)
Expired - Lifetime
Application number
US872605A
Other languages
English (en)
Inventor
Jacques Emile Jules Caruel
Armand Jean-Baptiste Lacroix
Herve Alain Quillevere
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.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA SAS
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 SNECMA SAS filed Critical SNECMA SAS
Application granted granted Critical
Publication of US3626444A publication Critical patent/US3626444A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

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
    • F23R3/30—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices
    • F23R3/32—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices being tubular

Definitions

  • a T-shaped liquid fuel prevaporizing device for a combustion chamber comprising a tubular shank projecting into the combustion chamber and two arms projecting from the downstream section of said shank to open into the combustion chamber, wherein overheating of the device is minimized by compartmenting the downstream section of the tubular shank by longitudinal partitions to form separate but intercommunicating passages which are selectively fed with combustion air alone and with fuel/air mixture.
  • Liquid fuel vaporizers consist of a T-shaped hollow structure having a shank projecting longitudinally within the combustion chamber and which, at one of its ends, communicates with the sources of liquid fuel and of combustion air, and, in the vicinity of its other end, opens into the combustion chamber through two lateral arms branching off from the said shank in a substantially symmetrical manner.
  • the present invention has for its object an improvement in combustion systems devices of the type mentioned above, and aims to combat the drawbacks just referred to by transferring the vaporization of the fuel into the most exposed zone of the vaporizer.
  • the shank of the T- shaped hollow structure is compartmented by means of a system of longitudinal partitions, in such a way as to define a central passage to be supplied solely with combustion air, and two lateral passages to be supplied simultaneously with combustion air and with liquid fuel, the said passages being intercommunicating and also communicating with the arms of the T-shaped hollow structure.
  • the compartmentation of the shank is effected by means of two flat longitudinal partitions running substantially parallel and bounding a central passage which is included between two lateral passages, the said partitions being perforated by communicating orifices in the region where the lateral ducts branch ofi.
  • the compartmentation of the shank is effected by means of an inner partition which is substantially coaxial with the axis of the shank and which defines the central passage, and by means of two transverse partitions which divide the peripheral space included between the shank and the inner partition into the lateral passages.
  • the crosssectional area of the central passage is greater than the sum of the cross-sectional areas of the lateral passages.
  • each of the lateral arms of the vaporizer are bent round so that its outlet end faces the annular end wall of the combustion chamber.
  • the fuel is then able to vaporize in this zone, this ensuring effective protection against occurrences of overheating.
  • FIG. 1 is a view, in fractional section taken along an axial plane, of a combustion system of known type, equipped with a liquid fuel vaporizer likewise of known type;
  • FIG. 2 is a view on a larger scale, and in longitudinal section, of the known type of prevaporizer shown in FIG. 1;
  • FIG. 3 is a view, in section taken along the line Ill-III of the known type of prevaporizer illustrated in FIG. 2;
  • FIG. 4 is a view similar to FIG. 2, showing a liquid fuel vaporizer in accordance with the present invention
  • FIG. 5 is a view, in section taken along the line VV of the liquid fuel vaporizer illustrated in FIG. 4;
  • FIG. 5a shows a view similar to FIG. 5, but according to a modified version of the present invention.
  • the general reference numeral 10 has been used to denote an already known T-shaped liquid fuel vaporizer fitted into a combustion system 11, likewise of known type.-
  • the combustion system comprises an annular combustion chamber having an outer casing 12a and an inner casing 12b which are substantially coaxial and which jointly define an annular space inside which two substantially coaxial walls 13a-13 bound an annular flame tube in which combustion occurs.
  • the latter flame tube is closed off in its upstream portion by an annular end wall or done 14 which cooperates with an annular supporting structure 15.
  • the annular end wall or dome 14 and the annular structure 15 are pierced by aligned orifices 16, 17 which are distributed uniformly about the axis x-x of the combustion chamber.
  • the reference numeral 18 has been used to denote a source of combustion supporter, for example compressed air.
  • the air travels in the annular space included between the casings 12a-12 and the flame tube, and penetrates into the combustion space in the form of primary air through orifices l6, and in the form of secondary air, cooling air and dilution air through orifices such as those' at 19a, 19b, 20a, 20b.
  • the combustion system 11 may be followed by an expansion turbine (not shown).
  • the liquid fuel vaporizer 10 in the example shown here forms part of a series of similar vaporizers, each of which is inserted through a respective orifice 17.
  • each fuel vaporizer 10 comprises a tubular shank 21 of which the upstream portion occupies the orifice 17 and the downstream portion branches off into two lateral arms 22aand 22bcurving back upstream at 23a, 23b.
  • a longitudinal partition 24 divides the shank 21 into two passages or compartments 25a, 25b, which communicate with the lateral arms 22a, 22b respectively by way of orifices 26a, 26b formed in the wall of the shank 21.
  • the shank 21 is closed off by an end plate 27.
  • the orifice 17 is so dimensioned as to render it possible to place a member 28 around the shank 21, which member may sometimes be integral with the shank.
  • This member possesses two extensions, 29 and 30, which define two passages 31 and 32 (see FIG. 1) permitting direct entry into the combustion space of a small fraction of the flow rate of primary air.
  • the reference numeral 33 denotes a source of liquid fuel.
  • the said air is at a relatively high temperature due to the compression it has previously undergone, and in certain instances due to the recuperation in a suitable heat exchanger (not shown) of a proportion of the heat from the exhaust gases from the turbine.
  • the amount of heat contained by it is sufficient, also taking into account the addition of extra heat originating in the combustion space and transmitted through the walls bounding the fuel vaporization 19, to bring about the complete vaporization of the liquid fuel.
  • the vaporized fuel/air'mixture is directed towards the upstream zone of the combustion space in such a way as to promote in an already known manner the recirculation upstream of a portion of the flow then undergoing combustion.
  • FIGS. 4 and 5 show an embodiment of a liquid fuel vaporizer in accordance with the present invention.
  • the vaporizer comprises a hollow T-shaped structure having a shank 21 and two lateral arms 22a, 22b, shank being surrounded by a passage 31 wherethrough a weak flow rate of air flows, as indicated by the arrows a, so as to form an insulating layer around the shank 21.
  • shank 21 is compartmented, at least along the downstream portion of its length, by a system of longitudinal partitions in'such a way as to define a central passage 35 and two flanking side passages 36a, 36b.
  • the said partitions may be flat and substantially parallel, as are, for example, the partitions 34a, 34b, shown in FIG. 5. But this arrangement is in no way mandatory, as is shown, in particular, by FIG. 5a, which relates to a modified version according to which the central passage 35 is bounded by a partition 37 which is substantially coaxial with the axis of the shank 21 while the flanking side passages 36a, 36b, result from the division into two passages for the peripheral space included between the shank 21 and the partition 37 by means of two transverse partitions 38, 39, which are substantially oppositely situated with respect to the axis.
  • the partitions 34a, 34b, (or the partition 37) are pierced by orifices 40a, 40b, which place the lateral arms 22a, 22b, the flanking side passages 36a, 36b and the central passage 35 all in communication with one another.
  • a liquid-fuel injector 41a, 41bis provided at the entrance to each of the flanking side passages 36a, 36!.
  • the central passage preferably has a cross-section area of exceeding that of the sum of the cross-sectional areas of the two flanking side lateral passages, so that only a small fraction of the flow rate of primary air, as indicated by the arrows A A is directed along the lateral passages 36a, 36binto which the injection of liquid fuel is carried out, while the greater portion of the said primary air, indicated by the arrow A,, passes along the central passage 35, which lacks a fuel injector.
  • the small fraction from the flow rate of primary air that is mixed with fuel in the flanking side passages is so set as to be just sufficient to prevent the occurrence of any possible phenomena ofcracking or cokin of the fuel.
  • the ow rate of an available along the flanking side lateral passages is insufficient to supply the amount of heat necessary for the complete vaporization of the fuel, so that the greater portion of the latter remains in the liquid state, even beyond the level x-y lt is consequently in the form of droplets that the fuel, after having reached the downstream zone of the shank 21, is drawn towards the lateral arms 22a22b, by the remainder, that is, by the greater portion of the flow rate of air, which is fed through the central duct and passes through the orifices 26a, 40a, 26b, 40b.
  • the vaporization of the fuel is thus retarded and is transferred to the lateral arms 22a, 22b, where it ensures an intense lowering of the temperature, and consequently effective protection against any overheating of the walls of the prevaporizer.
  • a combustion system having, in combustion, a combustion chamber including an annular end wall; a source of liquid fuel and a source of combustion air; and a plurality of tubular liquid fuel Vaporizers mounted to project into the combustion chamber from said annular end wall thereof, each of said fuel Vaporizers comprising: a tubular shank projecting longitudinally within the combustion chamber and having an open end adjacent said annular end wall and a closed end remote therefrom; two tubular arms each of which branches off laterally from said shank remote from said annular wall and has a free end which opens into the combustion chamber, said shank and said arms forming together an interconnected T-shaped hollow structure with an inlet opening at the open end of the shank and an outlet opening at the free end of each of said two arms;
  • partitions disposed'longitudinally within the shank of sub- 1 divide said shank into a central passage and two flanking side passages, said partitions being interrupted generally in the region of said laterally branching tubular areas to place said central passage in communication in said region with said flanking side passages and with said tubular arms;

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Spray-Type Burners (AREA)
  • Production Of Liquid Hydrocarbon Mixture For Refining Petroleum (AREA)
US872605A 1968-11-04 1969-10-30 Improvements in liquid fuel vaporizing combustion systems Expired - Lifetime US3626444A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR172477 1968-11-04

Publications (1)

Publication Number Publication Date
US3626444A true US3626444A (en) 1971-12-07

Family

ID=8656455

Family Applications (1)

Application Number Title Priority Date Filing Date
US872605A Expired - Lifetime US3626444A (en) 1968-11-04 1969-10-30 Improvements in liquid fuel vaporizing combustion systems

Country Status (4)

Country Link
US (1) US3626444A (de)
DE (1) DE1953671C3 (de)
FR (1) FR1590542A (de)
GB (1) GB1280715A (de)

Cited By (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3757522A (en) * 1971-07-16 1973-09-11 Moteurs D Aviat D Et Const Devices for pre-vaporising liquid fuel
FR2209042A1 (de) * 1972-08-10 1974-06-28 Rolls Royce
US3869865A (en) * 1972-06-23 1975-03-11 Snecma Devices for prevaporising liquid fuel
US4005572A (en) * 1975-04-18 1977-02-01 Giffhorn William A Gas turbine engine control system
US4742684A (en) * 1981-12-24 1988-05-10 Rolls-Royce Plc Fuel vaporizers for a gas turbine engine combustion engine
US5133192A (en) * 1989-08-31 1992-07-28 Rolls-Royce Plc Fuel vaporizer
US5156002A (en) * 1990-03-05 1992-10-20 Rolf J. Mowill Low emissions gas turbine combustor
US5377483A (en) * 1993-07-07 1995-01-03 Mowill; R. Jan Process for single stage premixed constant fuel/air ratio combustion
US5572862A (en) * 1993-07-07 1996-11-12 Mowill Rolf Jan Convectively cooled, single stage, fully premixed fuel/air combustor for gas turbine engine modules
US5613357A (en) * 1993-07-07 1997-03-25 Mowill; R. Jan Star-shaped single stage low emission combustor system
US5628182A (en) * 1993-07-07 1997-05-13 Mowill; R. Jan Star combustor with dilution ports in can portions
US5638674A (en) * 1993-07-07 1997-06-17 Mowill; R. Jan Convectively cooled, single stage, fully premixed controllable fuel/air combustor with tangential admission
US5651252A (en) * 1995-02-15 1997-07-29 Societe Nationale D'etude Et De Construction De Moteurs D'aviation S.N.E.C.M.A. Fuel injection assembly for a gas turbine engine
US5924276A (en) * 1996-07-17 1999-07-20 Mowill; R. Jan Premixer with dilution air bypass valve assembly
WO2000000772A2 (en) * 1998-06-12 2000-01-06 Precision Combustion, Inc. DRY, LOW NOx CATALYTIC PILOT
US6220034B1 (en) 1993-07-07 2001-04-24 R. Jan Mowill Convectively cooled, single stage, fully premixed controllable fuel/air combustor
US6925809B2 (en) 1999-02-26 2005-08-09 R. Jan Mowill Gas turbine engine fuel/air premixers with variable geometry exit and method for controlling exit velocities
FR3066009A1 (fr) * 2017-05-02 2018-11-09 Safran Helicopter Engines Canne de prevaporisation pour une turbomachine
US20230184438A1 (en) * 2019-10-08 2023-06-15 Safran Helicopter Engines Pre-vaporisation tube for a turbine engine combustion chamber

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2131790B1 (de) * 1971-02-19 1974-09-27 Snecma
DE2815916C2 (de) * 1978-04-13 1983-11-03 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Ringbrennkammer mit Brennstoff-Vorverdampfung für Gasturbinentriebwerke

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2956404A (en) * 1956-10-02 1960-10-18 Avco Mfg Corp Fuel vaporizer
US2982098A (en) * 1953-04-22 1961-05-02 Power Jets Res & Dev Ltd Liquid fuel vaporizing combustion systems

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2982098A (en) * 1953-04-22 1961-05-02 Power Jets Res & Dev Ltd Liquid fuel vaporizing combustion systems
US2956404A (en) * 1956-10-02 1960-10-18 Avco Mfg Corp Fuel vaporizer

Cited By (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3757522A (en) * 1971-07-16 1973-09-11 Moteurs D Aviat D Et Const Devices for pre-vaporising liquid fuel
US3869865A (en) * 1972-06-23 1975-03-11 Snecma Devices for prevaporising liquid fuel
FR2209042A1 (de) * 1972-08-10 1974-06-28 Rolls Royce
US4005572A (en) * 1975-04-18 1977-02-01 Giffhorn William A Gas turbine engine control system
US4742684A (en) * 1981-12-24 1988-05-10 Rolls-Royce Plc Fuel vaporizers for a gas turbine engine combustion engine
US5133192A (en) * 1989-08-31 1992-07-28 Rolls-Royce Plc Fuel vaporizer
US5156002A (en) * 1990-03-05 1992-10-20 Rolf J. Mowill Low emissions gas turbine combustor
US5628182A (en) * 1993-07-07 1997-05-13 Mowill; R. Jan Star combustor with dilution ports in can portions
US6220034B1 (en) 1993-07-07 2001-04-24 R. Jan Mowill Convectively cooled, single stage, fully premixed controllable fuel/air combustor
US5481866A (en) * 1993-07-07 1996-01-09 Mowill; R. Jan Single stage premixed constant fuel/air ratio combustor
US5572862A (en) * 1993-07-07 1996-11-12 Mowill Rolf Jan Convectively cooled, single stage, fully premixed fuel/air combustor for gas turbine engine modules
US5613357A (en) * 1993-07-07 1997-03-25 Mowill; R. Jan Star-shaped single stage low emission combustor system
US5377483A (en) * 1993-07-07 1995-01-03 Mowill; R. Jan Process for single stage premixed constant fuel/air ratio combustion
US5638674A (en) * 1993-07-07 1997-06-17 Mowill; R. Jan Convectively cooled, single stage, fully premixed controllable fuel/air combustor with tangential admission
US5477671A (en) * 1993-07-07 1995-12-26 Mowill; R. Jan Single stage premixed constant fuel/air ratio combustor
US5765363A (en) * 1993-07-07 1998-06-16 Mowill; R. Jan Convectively cooled, single stage, fully premixed controllable fuel/air combustor with tangential admission
US5651252A (en) * 1995-02-15 1997-07-29 Societe Nationale D'etude Et De Construction De Moteurs D'aviation S.N.E.C.M.A. Fuel injection assembly for a gas turbine engine
US5924276A (en) * 1996-07-17 1999-07-20 Mowill; R. Jan Premixer with dilution air bypass valve assembly
WO2000000772A2 (en) * 1998-06-12 2000-01-06 Precision Combustion, Inc. DRY, LOW NOx CATALYTIC PILOT
WO2000000772A3 (en) * 1998-06-12 2000-03-09 Precision Combustion Inc DRY, LOW NOx CATALYTIC PILOT
US6155819A (en) * 1998-06-12 2000-12-05 Precision Combustion, Inc. Dry, low NOx catalytic pilot
US6925809B2 (en) 1999-02-26 2005-08-09 R. Jan Mowill Gas turbine engine fuel/air premixers with variable geometry exit and method for controlling exit velocities
FR3066009A1 (fr) * 2017-05-02 2018-11-09 Safran Helicopter Engines Canne de prevaporisation pour une turbomachine
US20230184438A1 (en) * 2019-10-08 2023-06-15 Safran Helicopter Engines Pre-vaporisation tube for a turbine engine combustion chamber
US11841140B2 (en) * 2019-10-08 2023-12-12 Safran Helicopter Engines Pre-vaporization tube for a turbine engine combustion chamber

Also Published As

Publication number Publication date
FR1590542A (de) 1970-04-13
DE1953671A1 (de) 1970-05-06
DE1953671B2 (de) 1979-03-01
GB1280715A (en) 1972-07-05
DE1953671C3 (de) 1979-10-18

Similar Documents

Publication Publication Date Title
US3626444A (en) Improvements in liquid fuel vaporizing combustion systems
BR9812738A (pt) Aquecedor de processo, e, processo para proporcionar calor a uma reação de processo
US2687614A (en) Fuel admission device for resonance combustion apparatus
US2532709A (en) Liquid cooled baffles between mixing and combustion chambers
US2548087A (en) Vaporizer system for combustion chambers
US2996884A (en) Combustion chamber
US2982098A (en) Liquid fuel vaporizing combustion systems
US2949012A (en) Vaporisation burner device
US4275564A (en) Combustion chamber for gas turbine engines
NO854511L (no) Forbrenningsanordning for gassturbiner.
GB1392739A (en) Devices for pre-vaporising liquid fuel
GB712843A (en) Vaporising and combustion systems of gas turbine engines
EP3073096B1 (de) Verbessertes feuchtluftturbinensystem und abgasbehandlungssystem
CN113983462A (zh) 一种燃烧装置及燃气灶
US4400156A (en) Gas burner
US3270506A (en) Liquid-vapor fuel injector flameholder
US2635424A (en) Combustor for high flow velocities
US3931799A (en) Adiabatic integral intake and exhaust conduit for internal combustion engine
US2777291A (en) Combustion chamber with removable flame tubes
US2872906A (en) Method for the operation of a boiler and apparatus therefor
US2763582A (en) Apparatus and method of producing protective combustion atmospheres
CN216244272U (zh) 一种燃烧装置及燃气灶
GB527025A (en) Improvements in or relating to heating apparatus for the cabins of aircraft
JPS58182018A (ja) 燃焼装置
GB1390031A (en) Reheat system for a gas turbine engine