US3156094A - Catalytic ignition means for a jet engine thrust augmentation system - Google Patents

Catalytic ignition means for a jet engine thrust augmentation system Download PDF

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Publication number
US3156094A
US3156094A US239233A US23923362A US3156094A US 3156094 A US3156094 A US 3156094A US 239233 A US239233 A US 239233A US 23923362 A US23923362 A US 23923362A US 3156094 A US3156094 A US 3156094A
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US
United States
Prior art keywords
catalytic
gas stream
support member
flow
catalytic element
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
US239233A
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English (en)
Inventor
Dudley O Nash
John P Plungis
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.)
General Electric Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Priority to US239233A priority Critical patent/US3156094A/en
Priority to DEG39199A priority patent/DE1232403B/de
Priority to GB45593/63A priority patent/GB998295A/en
Priority to BE640189A priority patent/BE640189A/xx
Priority to FR954489A priority patent/FR1374905A/fr
Application granted granted Critical
Publication of US3156094A publication Critical patent/US3156094A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/26—Starting; Ignition
    • F02C7/264—Ignition
    • 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
    • F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
    • 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
    • F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
    • F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
    • F23R3/20—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants incorporating 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
    • F23R3/40—Continuous combustion chambers using liquid or gaseous fuel characterised by the use of catalytic means

Definitions

  • This invention relates to an improvement in jet engine thrust augmentation systems in general and, in particular, to catalytic ignition means for such a system having an improved service life and the capability of easy replacement.
  • a more specific object of the present invention is to provide a catalytic ignition means and mounting therefor wherein cooling flow around the catalytic material and holder is enhanced and replacement of the catalytic mateice rial, when it has deteriorated suificiently through use, is greatly simplified.
  • a further object of the present invention is to provide an improved catalytic ignition means in which the catalytic material or element is held in place by a dynamic loading torce arrangement whereby the wear factor on the element during operation is reduced and maximum efliciency is maintained during the life of the element.
  • a still further object of the present invention is to provide a mounting arrangement for a catalytic igniter element whereby the force of the high velocity hot gas stream impinging on the element will be maintained at a substantially uniform constant pressure during the operational life of the element to help to increase element life.
  • a preferred embodiment of the invention comprises an improved cat-alytic ignition device having a main body portion, a support member positioned within the body portion, a center bore through the support member, a plurality of diverging cooling air passages arranged normal to the flow direction of a hot gas stream passing through the center bore, with an annular space provided between the support member and the body portion in flow communication with the passages, and a flow-permeable catalytic element located in the support member and positioned in the path of the hot gas stream.
  • a free-floating, perforated metering disk is arranged in overlying relationship with the catalytic element.
  • the metering disk is dynamically loaded against the catalytic element so as to ensure a sub stantially constant gas stream load upon the catalytic element, regardless of the effect of the hot gas stream tending to reduce the dimensions of the element, and to prevent flow fluctuations which have been shown to have a tendency to reduce life.
  • the parts of the described catalytic ignition device, including the supporting members, are maintained in an assembled relationship by removable retainers which enable easy replacement of the catalytic material or element.
  • FIG. 1 is a side elevation view of a jet engine exhaust pipe in which is mounted afterburning or thrust augmentation combustion apparatus in combination with the improved catalytic ignition means of the subject invention
  • PEG. 2 is an enlarged side view, partially in cross-section, of the improved catalytic ignition means indicating the manner in which it is mounted to the flameholder means shown in FIGURE 1;
  • FIG. 3 is an enlarged end view illustrating the direction of cooling flow through the improved catalytic ignition means of the present invention.
  • FIG. 4 is an exploded, assembly View illustrating the components comprising the supporting portions of the catalytic ignition means and the placement of the catalytic element and retaining means.
  • FIGURE 1 depicted schematically is a jet engine tailpipe or exhaust duct having an outer casing or shell 10.
  • the tailpipe may include an annular center body 14 which divides the exhaust area into an annulus through which flows a stream of hot combustible gases indicated by the solid arrows, which gases exit from the exhaust duct in the form of propulsive jet.
  • fuel injection means 16 is provided which projects transversely of the combustible gas stream.
  • a flame stabilizing device such as the annular flameholder assembly indicated generally at 18 inserted in the combustible gas stream downstream of the fuel injection means.
  • the fiameholder annular gutters typically are V-shaped in cross-section. Affixed to one of the V-shaped gutters and indicated generally at 20 is the improved catalytic ignition means which comprises the subject of the present invention.
  • our improved catalytic ignition means 20 includes a cylindrical body portion or sleeve 21 having imperforate walls.
  • the sleeve is permanently attached to the fiameholder gutter by welding or brazing and extends in an upstream direction with its axis substantially parallel to the jet engine duct centerline 10.
  • the body or sleeve 21 includes an internal shoulder portion 22 which is adapted to abut a holder or support member indicated generally at 24.
  • the holder member comprises a reduced cylindrical portion 26 extending in an upstream direction from an enlarged downstream portion 28.
  • the downstream portion 28 contacts the upstream face of the shoulder portion 22 and thus is retained in the cylindrical sleeve 21 against the force of the gas stream flowing in a direction indicated by the large arrow.
  • the enlarged portion 28 of the holder member 24 also has a central opening 30 through which the hot gas stream will pass.
  • the opening 30 communicates with an internal bore 34 in the upstream portion of the holder member in which is adapted to be positioned the catalytic material or element.
  • the catalyst comprises a plurality of platinum or platinum containing alloy disks or circular pieces of small wire mesh arranged in a pad or core 36.
  • the pad 36 could also comprise a single flow permeable member having substantial thickness in the direction of flow.
  • insulating means 38-38 Deposited upon the surfaces of the core or pad 36, or in the form of separate disks or wafers, are insulating means 38-38, one of which is located on the upstream side, the other on the downstream side.
  • the element is cylindrical, substantially wafer-like, and rests within the internal bore of the holder member on the surface 39.
  • a metering disk 40 Upstream of the insulating means on or in front of the catalytic element 36 is located a metering disk 40 having a plurality of openings 41. While it is well known in the prior art to provide some sort of retaining cover or cap to prevent the catalytic element from being blown out by the high velocity gas stream, heretofore such covers or caps have been rigidly fastened to or supported within the catalytic element support means. However, it will be noted that in the present invention, the metering disk 40 merely rests against the platinum pad or core pieces being dynamically loaded thereon by means of the force exerted by the gas flow.
  • the present invention utilizes dynamic pressure loading on the metering disk to maintain the catalytic element against the shoulder 39.
  • the pressure loaded, floating metering disk of the present invention is free to move as the screen or mesh pad becomes compacted and this maintains a constant level clamping force during the life of the catalytic element.
  • the improved catalytic ignition means described herein has shown not only to be capable of longer operational life but the design has made possible more consistency of life among a multiplicity of catalytic ignition means utilized in a significant number of production type jet engine installations. In this manner, although other methods have been suggested whereby the life of a specific igniter has been improved, up until the present invention attainment of consistency in igniter life has been lacking.
  • the upstream portion 26 of the holder member 24 is smaller in diameter than the inner diameter of the body member 21 upstream of the shoulder 22. This provides an annular fiow passage 42 around the outside of the holder member.
  • a plurality of diverging cooling air passages 44 at the downstream end of the reduced portion 26 of the holder member, i.e., the passages are located between the reduced portion and the enlarged portion 28 of the holder member 24.
  • the passages extend from the bottom or downstream end of the annular flow passage 42 to the center bore 30 of the holder member, i.e., normal to the gas flow through the igniter means.
  • the airflow after passing through the annular passage 42, exits through the diverging passages, cooling the holder and the periphery of the center bore since the passages 44 merge into an annulus adjacent the rim of the center bore 30.
  • the described arrangement provides a unique, more efiicient cooling flow path for the catalyst holder 24, wherein the cooling air is directed radially inward through diverging passages and discharges as a cooling film over the periphery of the center bore in the holder through which passes the hot gas stream. It has proved to be capable of eliminating substantially all severe jet engine afterburner catalytic igniter burning problems.
  • Still another feature of the present invention is the means whereby the catalytic element can be easily replaced.
  • the catalytic element which in the preferred form comprises one or more platinum or platinum containing alloy mesh or gauze pads, slowly deteriorates with use. That is, the diameter of the fine platinum wires comprising the mesh will be slowly reduced with use which will result in reduced catalytic activity and further loss of platinum.
  • one of the objects of the present invention is to develop means for easily and periodically reloading the catalyst holder with a new element without the need for destroying the supporting body members or holders or requiring a complicated disassembly procedure.
  • a plurality of removable retainer means in the form of wire clips generally indicated at 48.
  • FIGURE 4 also illustrates clearly the manner in which the catalytic element or pad 36 and the metering disk 46 are easily assembled using the clips or retainers 43.
  • Another advantage gaincd through easier replacement of the catalytic element is maintenance of a high level of catalytic activity since the platinum gauze or mesh is more likely to be replaced periodically before an unwarranted amount of loss of catalytic activity has taken place through reduction of the amount of the catalytic material in the element.
  • a by-product of this arrangement is the economic advantage realized by the ability to utilize the used platinum in the element replaced since it usually comprises about 80% of the cost of new material of the new element.
  • An improved catalytic ignition device for use in a high velocity, continuous flow combustible gas stream, said ignition device comprising:
  • a generally cylindrical hollow body member having an imperforate wall and including a shoulder located internally and intermediate the open ends thereof;
  • a support member positioned within said body member and including a central opening therethrough, said support member forming an annular passage with the interior surface of said imperforate wall;
  • a free-floating perforated metering disk overlying the catalytic element and presenting a surface normal to the gas stream, said metering disk being dynamically loaded against the catalytic element by the force of said gas stream flowing axially through said openended hollow body member;
  • An improved catalytic ignition device for use in a high velocity, axial-flow combustible gas stream, said ignition device comprising:
  • An improved catalytic ignition device for use in a high velocity, continuous flow combustible gas stream, said ignition device comprising:
  • a generally cylindrical body portion having an imperferate wall, said body portion being open at either end and including a shoulder internally thereof;
  • a support member positioned within said body portion, said support member having an enlarged portion adapted to be positioned against said shoulder and a reduced portion extending upstream thereof;
  • a free-floating perforated metering disk overlying the catalytic element and having a face normal to the gas stream, said metering disk being dynamically loaded against the catalytic element by the force of the gas stream;

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Exhaust Gas After Treatment (AREA)
US239233A 1962-11-21 1962-11-21 Catalytic ignition means for a jet engine thrust augmentation system Expired - Lifetime US3156094A (en)

Priority Applications (5)

Application Number Priority Date Filing Date Title
US239233A US3156094A (en) 1962-11-21 1962-11-21 Catalytic ignition means for a jet engine thrust augmentation system
DEG39199A DE1232403B (de) 1962-11-21 1963-11-18 Katalytische Zuendvorrichtung
GB45593/63A GB998295A (en) 1962-11-21 1963-11-19 Improvements in catalytic ignition means for a jet engine thrust augmentation system
BE640189A BE640189A (en:Method) 1962-11-21 1963-11-20
FR954489A FR1374905A (fr) 1962-11-21 1963-11-21 Dispositif catalytique d'allumage pour un système d'augmentation de poussée d'un moteur à réaction

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US239233A US3156094A (en) 1962-11-21 1962-11-21 Catalytic ignition means for a jet engine thrust augmentation system

Publications (1)

Publication Number Publication Date
US3156094A true US3156094A (en) 1964-11-10

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US239233A Expired - Lifetime US3156094A (en) 1962-11-21 1962-11-21 Catalytic ignition means for a jet engine thrust augmentation system

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US (1) US3156094A (en:Method)
BE (1) BE640189A (en:Method)
DE (1) DE1232403B (en:Method)
GB (1) GB998295A (en:Method)

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3352113A (en) * 1964-08-19 1967-11-14 Rolls Royce Reheat combustion equipment
US3355885A (en) * 1964-11-19 1967-12-05 Rolls Royce Prime mover ignition device
US3765178A (en) * 1972-09-08 1973-10-16 Gen Electric Afterburner flameholder
US4901527A (en) * 1988-02-18 1990-02-20 General Electric Company Low turbulence flame holder mount
US5593299A (en) * 1991-01-09 1997-01-14 Pfefferle; William C. Catalytic method
WO1999056064A1 (en) * 1998-04-30 1999-11-04 Catalytica Combustion Systems, Inc. Support structures for a catalyst
US20020110501A1 (en) * 2000-11-13 2002-08-15 John Barnes Thermally tolerant support structure for a catalytic combustion catalyst
RU2232349C1 (ru) * 2002-12-23 2004-07-10 Государственное унитарное предприятие Тушинское машиностроительное конструкторское бюро "Союз" - дочернее предприятие Федерального государственного унитарного предприятия "Российская самолето-строительная корпорация "МиГ" Каталитический воспламенитель
US20050011194A1 (en) * 2003-07-14 2005-01-20 Siemens Westinghouse Power Corporation Pilotless catalytic combustor
CN112502839A (zh) * 2020-11-27 2021-03-16 陕西航空电气有限责任公司 一种航空发动机催化点火装置

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2658742A (en) * 1950-01-09 1953-11-10 Harold R Suter Catalytic fume incineration
US2964907A (en) * 1957-11-15 1960-12-20 Rolls Royce Combustion stabilising device for combustion equipment
US2970439A (en) * 1949-09-13 1961-02-07 Walter G Berl Catalytic igniter for ram-jet burner
US2972227A (en) * 1956-07-05 1961-02-21 Bristol Siddeley Engines Ltd Means for supplying a rocket motor with liquid fuel and concentrated hydrogen peroxide as propellant
US3032991A (en) * 1959-10-01 1962-05-08 Gen Electric Combustion sustaining means for continuous flow combustion systems

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1281054A (fr) * 1960-02-17 1962-01-08 Rolls Royce Perfectionnements aux appareillages de combustion, par exemple pour moteur à turbine à gaz

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2970439A (en) * 1949-09-13 1961-02-07 Walter G Berl Catalytic igniter for ram-jet burner
US2658742A (en) * 1950-01-09 1953-11-10 Harold R Suter Catalytic fume incineration
US2972227A (en) * 1956-07-05 1961-02-21 Bristol Siddeley Engines Ltd Means for supplying a rocket motor with liquid fuel and concentrated hydrogen peroxide as propellant
US2964907A (en) * 1957-11-15 1960-12-20 Rolls Royce Combustion stabilising device for combustion equipment
US3032991A (en) * 1959-10-01 1962-05-08 Gen Electric Combustion sustaining means for continuous flow combustion systems

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3352113A (en) * 1964-08-19 1967-11-14 Rolls Royce Reheat combustion equipment
US3355885A (en) * 1964-11-19 1967-12-05 Rolls Royce Prime mover ignition device
US3765178A (en) * 1972-09-08 1973-10-16 Gen Electric Afterburner flameholder
US4901527A (en) * 1988-02-18 1990-02-20 General Electric Company Low turbulence flame holder mount
US5593299A (en) * 1991-01-09 1997-01-14 Pfefferle; William C. Catalytic method
WO1999056064A1 (en) * 1998-04-30 1999-11-04 Catalytica Combustion Systems, Inc. Support structures for a catalyst
US20020110501A1 (en) * 2000-11-13 2002-08-15 John Barnes Thermally tolerant support structure for a catalytic combustion catalyst
US7163666B2 (en) 2000-11-13 2007-01-16 Kawasaki Jukogyo Kabushiki Kaisha Thermally tolerant support structure for a catalytic combustion catalyst
RU2232349C1 (ru) * 2002-12-23 2004-07-10 Государственное унитарное предприятие Тушинское машиностроительное конструкторское бюро "Союз" - дочернее предприятие Федерального государственного унитарного предприятия "Российская самолето-строительная корпорация "МиГ" Каталитический воспламенитель
US20050011194A1 (en) * 2003-07-14 2005-01-20 Siemens Westinghouse Power Corporation Pilotless catalytic combustor
US6923001B2 (en) * 2003-07-14 2005-08-02 Siemens Westinghouse Power Corporation Pilotless catalytic combustor
CN112502839A (zh) * 2020-11-27 2021-03-16 陕西航空电气有限责任公司 一种航空发动机催化点火装置

Also Published As

Publication number Publication date
DE1232403B (de) 1967-01-12
BE640189A (en:Method) 1964-03-16
GB998295A (en) 1965-07-14

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