US3768251A - Fixing of fuel injection manifolds into combustion chambers - Google Patents

Fixing of fuel injection manifolds into combustion chambers Download PDF

Info

Publication number
US3768251A
US3768251A US00218811A US3768251DA US3768251A US 3768251 A US3768251 A US 3768251A US 00218811 A US00218811 A US 00218811A US 3768251D A US3768251D A US 3768251DA US 3768251 A US3768251 A US 3768251A
Authority
US
United States
Prior art keywords
manifold
plane
link rods
reference structure
centerline
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
US00218811A
Other languages
English (en)
Inventor
A Camboulives
R Vandenbroucke
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
Etude Construction Moteurs D A
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 Etude Construction Moteurs D A filed Critical Etude Construction Moteurs D A
Application granted granted Critical
Publication of US3768251A publication Critical patent/US3768251A/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
    • F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
    • 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
    • F02C7/22—Fuel supply systems
    • F02C7/222—Fuel flow conduits, e.g. manifolds

Definitions

  • ABSTRACT A device for securing within a combustion chamber an injection manifold which is connected to the wall of the said chamber by a pipe section preferably curved into a swan-neck," said device comprising a linkage system connected to the manifold and to a reference structure such as a stabilizer in such a way as to permit the manifold to undergo displacement parallel to itself by maintainingtwo points on the manifold in an axial plane of the chamber that contains the point where the pipe section passes through the said wall.
  • the linkage system may comprise two link rods contained within this plane and pivotally mounted about axes perpendicular to the said plane, and several pairs of further link rods pivotally attached by swivel or universal joints.
  • the invention relates tothe fixing of an injection manifold, which operates to inject fuel, into a space where its combustion takes place.
  • a combustion chamber this may more especially be a main combustion chamber or an afterburner Jet-pipe for an aircraft powerplant.
  • the operating cycle of a turbojet engine is greatly improved by a reheat system applied to the gases exiting from the turbine of the turbojet engine, i.e., by the combustion in the midst of these gases of fuel injected into a so-called afterburner jet-pipe.
  • the thrust of the turbojet engine is thus increased to remarkable proportions.
  • the fuel is injected into the afterburner jet-pipe via one or more injectors located either'upstream of a flame stabilizer or inside the said stabilizer.
  • the injectors are generally arranged in the form of a circular manifold within the afterburner jet-pipe.
  • the present invention aims to solve these problems by providing a practically isostatic suspension system for the injection manifold, this system eliminating the major stresses that are of thermal origin by permitting limited displacements of the manifold in relation to adjacent parts to which the manifold is operatively linked.
  • the manifold is connected to a reference structure (positioned inside the combustion chamber) by means of a jointed linkage system: which permits the manifold to undergo displacement parallel to itself by keeping two points on the latter in a single axial plane of the said chamber, which plane contains the point where the length of feed-pipe for the manifold passes through the wall of the combustion chamber.
  • the junction of this length of piping with the injection manifold will preferably be offset in a transverse direction with reference to the point of penetration, in such a way as not to be located in this axial plane itself.
  • the length of piping is, for example, bent in a swan-neck shape.
  • the linkage system comprises two link rods which connect to the reference structure the two points on the manifold respectively which are located in the said axial plane, each of the rods being pivotally connected at either end about an axis perpendicular to the said plane, and the system also comprises a plurality of pairs of link rods arranged symmetrically with reference to the said plane, these being connected by swivel or universal joints to the manifold and the reference structure. All the said rods are preferably mounted parallel to the axis of the combustion chamber. They are preferably positioned equidistantly.
  • the reference structure is preferably a flame stabilizer.
  • a displacement by a few millimeters of the manifold (this being parallel to the same) with reference to the stabilizer which acts to support it does not harm the proper operation of the assembly, and introduces neither stresser nor deformations into the manifold, this being whatever the difference in temperature between the manifold and the stabilizer that brought about this relative displacement.
  • the injection manifold itself acts as a support means for a further combustion-chamber member, for example for an annular member called an anvil, against which the manifold hurls the fuel to ensure its pulverization, the manifold being connected to the said chamber by further link rods pivotally connected to the said member and to the manifold about tangentially arranged axes.
  • FIG. 1 is a view of a diagrammatic axial section taken through an afterburner jet-pipe of an aircraft jet turbine engine
  • FIG. 2 is a section on a larger scale taken along the line II'-II in FIG. 1;
  • FIGS. 3, 4 and 5 are sections on a still larger scale taken along the lines III-III, IVI ⁇ and VV respectively in FIG. 2;
  • FIGS. 3a, 4a and 5a are sections taken along the lines IIIa--IIIa, IVa-IVa and Va-Va respectively of FIGS. 3, 4 and 5;
  • FIGS. 6 and 7 are sections taken along the lines VI-VI and VIIVII respectively in FIG. 5;
  • FIG. 8 is a section taken along the line VIII-VIII in FIG. 2; and showing a modification
  • FIG. 9 is a fractional view similar to FIG. 2, showing a further modification.
  • FIG. 9a is a view obtained looking along the arrow IX in FIG. 9.'
  • the afterburner jet-pipe shown in FIG. 1 comprises a wall 1 of revolution about the axis X-X'. It receives a hot-gas flow coming from the turbine of an aircraft jet engine (not shown) and flowing in the direction of the arrow F The gases of said flow are reheated in the jetpipe by the combustion of fuel injected via a manifold 2, and they exit from the jet-pipe following the arrow F so as to be ejected into an exhaust nozzle (not shown).
  • the injection manifold 2 is a circular tube coaxial with the jet-pipe and provided on its upstream face with small nozzles 2a (FIG. 2) by which it injects fuel which undergoes atomization against an annular anvil 3 positioned further upstream.
  • the said anvil 3 has a U-shaped cross-section the branches of which are turned upstream; its shape is illustrated more clearly in FIGS. 3 and 3a. In other embodiments (not shown) the branches of the U may be turned downstream. Downstream of the injection manifold 2 there is a stabilizer ring 4 arranged which fulfils the role of a flame stabilizer.
  • the stabilizer has a cross-section in the form of a V with a rounded apex, the branches of which are turned downstream as shown in FIGS. 3 and 3a.
  • the stabilizer ring 4 is attached to the wall 1 of the afterburner jet-pipe in a well-known manner by means of an arrangement of link rods of the type described and shown in the above-mentioned U.S. Pat. No. 3,102,392, one of which is fractionally illustrated at 4a in FIG. 4.
  • the injection manifold 2 is fed with fuel by way of piping which comprises a swan-neck section 5 (FIG. 2) which passes through the wall 1 of the afterburner jet-pipe and is connected by other lengths, including an elbow shown at 6, to a pressurized-fuel source (not shown).
  • the section 5 communicates with the injection manifold 2 by a three-way junction 5a, and with the elbow 6 by ajunction 5b positioned in line with the wall 1, which is clamped between a sleeper nut 50 and a ro? tating nut 5d.
  • the junction 5b has its axis arranged perpendicularly to the wall 1, and A denotes the point of intersection between the axis of the junction 5b and the neutral surface of the wall 1.
  • the manifold 1 and the section 5 are configured so that the clamping of the wall 1 between the two nuts 50 and 5d corresponds, in the absence of any other suspension system for the manifold and when the afterburner jet-pipe is cold, to a position of the manifold which is such that it will be centred on the axis X-X and positioned in a plane perpendicular to the said axis.
  • the injection manifold 2 is connected to the stabilizer ring 4 by two link rods pivotally connected to the manifold about tangential axes at two respective points B and C located in an axial plane P which passes through the point A, and by four pairs of rods attached by universal joints to the manifold at points D and E, F and G, H and I, J and K, which are symmetrical with reference to the said axial plane.
  • the two rods pivotally connected at B and C are likewise connected to the stabilizer ring 4 about tangential axes, and the other rods are likewise attached by universal joints to the stabilizer ring. All the rods are mounted parallel to the axis X-X' of the afterburner pipe.
  • the points B, D, F, H, J, K, I, G and E are arranged at the vertices of a nine-sided regular polygon the tenth point of attachment C, diametrically opposite the point B, is not located at a vertex of the said polygon, and is positioned at an equal distance from the two adjoining points J and K. Since the point of attachment B is located in the plane P which contains the axis XX' and the point A, the junction 5a is offset away from the said plane, to the end of the length of pipe 5 bent over like a swan-neck.”
  • the manifold 2 comprises at C a machined sleeve 7 (FIGS. 4 and 4a) carrying a projecting yoke 7a turned downstream and, in respect of the other pivotal points of the rods, nine sleeves 8 each carrying a yoke 8a pointing downstream and a yoke 8b pointing upstream (FIGS. 3, 3a and 5, 5a).
  • the machined sleeves 7 and 8 are joined by a welding process to bent pipe sections 9 (FIG. 2) so as to constitute the manifold 2 connected to the junction 5a.
  • the link rod 10 joining the point B of the manifold 2 to the stabilizer ring 4 is pivotally connected to the latter about a pin 10a arranged tangentially and supported by a yoke 11 welded to the stabilizer ring.
  • the rod 10 is pivotally connected to the manifold 2 about a pin 10b likewise arranged tangentially (i.e., mounted perpendicularly to the axial plane P) and carried by the yoke 8a.
  • the point C is similarly attached to the stabilizer ring by a rod 12 (FIGS.
  • the rods 10 and 12 form a fork at their end adjacent to the burner ring, this making it possible to arrange between the branches of this fork, in the centre of the pins 10a and 12a, rods such as those at 4a (FIG. 4) which act to secure the burner ring 4 to the wall 1.
  • Each of the pins 10a, 10b, 12a, 12b is provided at one end with a hexagonal head 13 and at the other end with a grooved collar 14, in the groove of which is fitted a lock-pin 15 in the form ofa U which passes through the pin and the collar.
  • the thermal expansion of the manifold 2 displaces respectively: point B to B point C to C and the centre 0 of the manifold to O virtually in the direction of the axis of the junction 5b and of the straight part of the pipe section 5, the slanting portion of which is as short as possible for the reason given above.
  • the displacement of the points B and C of the manifold is therefore orthogonal to the pins 10b and 12b, so that the rods 10 and 12 pivot without deformation about the pins 10a and 12a supported by the burner ring 4.
  • the manifold 2 will not shift appreciably in the direction of the axis X-X since the link rods 10 and 12 are, when cold, parallel to this axis. Whatever eventuates, the manifold 2 will undergo displacement parallel to itself.
  • the other attachment points for the manifold i.e., the points D, E, F, G, H, I, J and K, are positioned outside the axial plane P passing through the point A.
  • the said points of the manifold were fixed to the stabilizer ring 4 by link rods pivotally connected about tangential axes as are'the rods 10 and 12, then stresses giving rise to deformations would occur in the manifold 2 and in its suspension system, since the displacements of the manifold parallel to itself would not at these points be orthogonal to the tangential axes of articulation.
  • each of the said points on the manifold is connected to the stabilizer ring 4 by a link rod 16 (FIGS.
  • Each of the cylindrical plugs 17, 18 is traversed transversely, at a right angle to its axis, by an oblong opening 17a, 18a the width of which is adequate to receive, with a degree of play, the flattish tip 16c, 16d of the rod 16, and the length of which is sufficient to allow the travel of this rod in correspondence with the highest temperatures likely to prevail in the afterburner jet-pipe.
  • the plug 17 is mounted in a yoke 19 similar to the yokes 11 and 11a and is welded on the stabilizer ring 4; the yoke 18 is mounted pivotally in the yoke 8a.
  • Each of the two plugs 17 and 18 of each rod 16 therefore rotates in its respective yoke so that the pins 16a and 16b will be continuously orthogonal to the movement of the articulation point of this rod on the manifold 2, which expands because of its rise in temperature.
  • the annular anvil 3 has, as had already beenindicated, a U-shaped section an active pulverizing surface of which, constituted by the base of the U, forms a flat ring parallel to the mean plane of the manifold 2 which is facing it.
  • the said flat ring is pierced, opposite each of the points C, D, E, F, G, H, I, J and K, by an opening 20 which affordspassage to a link rod 21 which is at its downstream end pivotally attached about pin 21a supported by the yoke 8b, and at its upstream end about pin 21b supported by two corner-plates 22 welded to the inner side of the anvil body 3.
  • the pins 21a and 21b are held in place by respective traversing pins 23, which are themselves kept in place by spot welds 24 (FIGS. 6 and 7).
  • FIG. 8 illustrates a modification in which the junctions 8 positioned at the points .I and K are not connected by rods such as those at 16 to the stabilizer ring 4, but nevertheless support the pivotal pin 21a of a rod 21 which forms part of the rods supporting the anvil body 3.
  • the injection manifold 2 is therefore only connected to the stabilizer ring 4 by two rods l0, l2 and three pairs of rods 16.
  • the points such as those at B, CD, E, F, G, H, I, J and K may be located at ten vertices of regular polygon, the diametrically opposite points B and C being naturally located in the diametral plane P which contains the point A.
  • the pipe section 5 might be offset upstream or downstream along the after-' burner jet-pipe provided that the points B and C upon assembly are positioned in the axial plane P which contains the point A.
  • the swan-neck pipe section might also be replaced (FIG. 9) by a section 5' bifurcated into a V, the junction where it passes through the wall Sb being a Y junction and the two branches of the section 5 being joined to the injection manifold 2 by two junctions S'a and 5's respectively, arranged symmetrically to the plane that contains the axis X-X' and the centre of junction Sb.
  • the section 5' may also be offset upstream or downstream, as is shown in FIG. 9a.
  • an arrangement for fixing the fuel injection manifold within the casing wall comprising a pair of link rods connecting said manifold to said reference structure and extending on each side of the centerline in a plane which contains the centerline and the point of penetration, means mounting both ends of each said link rod for pivotal movement about axes perpendicular to said plane, a plurality of pairs of further link rods connecting said manifold to said reference structure and arranged symmetrically about said plane, and means mounting each end of each said further link rod for swivelling movement.
  • said manifold is of circular form and the swivelling attachment points on the manifold of said further link rods form, along with one of the points of the said manifold that are located in said plane, the vertices of a regular polygon comprising an odd number of sides.

Landscapes

  • 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)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)
US00218811A 1971-01-19 1972-01-18 Fixing of fuel injection manifolds into combustion chambers Expired - Lifetime US3768251A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR7101683A FR2122308B1 (enrdf_load_stackoverflow) 1971-01-19 1971-01-19

Publications (1)

Publication Number Publication Date
US3768251A true US3768251A (en) 1973-10-30

Family

ID=9070516

Family Applications (1)

Application Number Title Priority Date Filing Date
US00218811A Expired - Lifetime US3768251A (en) 1971-01-19 1972-01-18 Fixing of fuel injection manifolds into combustion chambers

Country Status (4)

Country Link
US (1) US3768251A (enrdf_load_stackoverflow)
DE (1) DE2202508C3 (enrdf_load_stackoverflow)
FR (1) FR2122308B1 (enrdf_load_stackoverflow)
GB (1) GB1329944A (enrdf_load_stackoverflow)

Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5001897A (en) * 1989-12-20 1991-03-26 United Technologies Corporation Augmentor spray ring mount
US5127224A (en) * 1991-03-25 1992-07-07 United Technologies Corporation Spray-ring mounting assembly
US5271218A (en) * 1992-05-28 1993-12-21 Gerneral Electric Company Off-engine mounting system for steam and gaseous fuel manifolds of marine and industrial gas turbine engines
US6367240B1 (en) * 1998-06-22 2002-04-09 General Electric Company Air manifold system
US20050188699A1 (en) * 2004-02-27 2005-09-01 Pratt & Whitney Canada Corp. Apparatus for fuel transport and the like
US20060277913A1 (en) * 2005-06-14 2006-12-14 Pratt & Whitney Canada Corp. Internally mounted fuel manifold with support pins
US20110120142A1 (en) * 2005-01-14 2011-05-26 Lev Alexander Prociw Gas turbine engine fuel conveying member
US20120186257A1 (en) * 2006-10-24 2012-07-26 Jason Fish Gas turbine internal manifold mounting arrangement
US8418468B2 (en) 2010-04-06 2013-04-16 General Electric Company Segmented annular ring-manifold quaternary fuel distributor
US8438852B2 (en) 2010-04-06 2013-05-14 General Electric Company Annular ring-manifold quaternary fuel distributor
US20130180253A1 (en) * 2012-01-13 2013-07-18 General Electric Company System and method for supplying a working fluid to a combustor
US20150082770A1 (en) * 2013-09-20 2015-03-26 Mitsubishi Hitachi Power Systems, Ltd. Dual-Fuel Burning Gas Turbine Combustor
US9267436B2 (en) * 2013-03-18 2016-02-23 General Electric Company Fuel distribution manifold for a combustor of a gas turbine
US11156162B2 (en) * 2018-05-23 2021-10-26 General Electric Company Fluid manifold damper for gas turbine engine
CN114876646A (zh) * 2022-07-11 2022-08-09 成都中科翼能科技有限公司 一种燃气轮机燃油总管的支撑结构及燃油总管总成

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4064691A (en) * 1975-11-04 1977-12-27 General Electric Company Cooling of fastener means for a removable flameholder
FR2586792B1 (fr) * 1985-09-03 1989-06-16 Snecma Dispositif de liaison entre un anneau bruleur ou accroche-flammes en materiau composite et un canal de chambre de post-combustion d'un turboreacteur
GB2298916B (en) * 1995-03-15 1998-11-04 Rolls Royce Plc Annular combustor
CN114165813B (zh) * 2021-12-03 2022-08-30 北京航空航天大学 一种双油路供油的气动辅助一体化支板稳定器
CN114412646B (zh) * 2022-02-18 2024-03-19 中国航发贵阳发动机设计研究所 一种加力外圈总管的固定结构

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB821286A (en) * 1956-06-05 1959-10-07 Rolls Royce Improvements in or relating to reheat combustion equipment of jet-propulsion engines
US3056261A (en) * 1959-09-01 1962-10-02 Gen Electric Flameholder configuration
US3102392A (en) * 1959-04-21 1963-09-03 Snecma Combustion equipment for jet propulsion units
US3646763A (en) * 1970-05-25 1972-03-07 Gen Electric Gas turbine engine with improved afterburner

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1477974A (fr) * 1966-04-28 1967-04-21 United Aircraft Corp Perfectionnements aux dispositifs porte-flamme de post-combustion pour moteur à réaction

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB821286A (en) * 1956-06-05 1959-10-07 Rolls Royce Improvements in or relating to reheat combustion equipment of jet-propulsion engines
US3102392A (en) * 1959-04-21 1963-09-03 Snecma Combustion equipment for jet propulsion units
US3056261A (en) * 1959-09-01 1962-10-02 Gen Electric Flameholder configuration
US3646763A (en) * 1970-05-25 1972-03-07 Gen Electric Gas turbine engine with improved afterburner

Cited By (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5001897A (en) * 1989-12-20 1991-03-26 United Technologies Corporation Augmentor spray ring mount
US5127224A (en) * 1991-03-25 1992-07-07 United Technologies Corporation Spray-ring mounting assembly
US5271218A (en) * 1992-05-28 1993-12-21 Gerneral Electric Company Off-engine mounting system for steam and gaseous fuel manifolds of marine and industrial gas turbine engines
US6367240B1 (en) * 1998-06-22 2002-04-09 General Electric Company Air manifold system
US7654088B2 (en) * 2004-02-27 2010-02-02 Pratt & Whitney Canada Corp. Dual conduit fuel manifold for gas turbine engine
US20050188699A1 (en) * 2004-02-27 2005-09-01 Pratt & Whitney Canada Corp. Apparatus for fuel transport and the like
US8276387B2 (en) * 2005-01-14 2012-10-02 Pratt & Whitney Canada Corp. Gas turbine engine fuel conveying member
US20110120142A1 (en) * 2005-01-14 2011-05-26 Lev Alexander Prociw Gas turbine engine fuel conveying member
US8171739B2 (en) 2005-06-14 2012-05-08 Pratt & Whitney Canada Corp. Internally mounted fuel manifold with support pins
EP1734307A3 (en) * 2005-06-14 2009-08-12 Pratt & Whitney Canada Corp. Internally mounted fuel manifold with support pins
US7540157B2 (en) 2005-06-14 2009-06-02 Pratt & Whitney Canada Corp. Internally mounted fuel manifold with support pins
WO2006133541A1 (en) * 2005-06-14 2006-12-21 Pratt & Whitney Canada Corp. Internally mounted fuel manifold with support pins
US20060277913A1 (en) * 2005-06-14 2006-12-14 Pratt & Whitney Canada Corp. Internally mounted fuel manifold with support pins
US20090199562A1 (en) * 2005-06-14 2009-08-13 Jason Araan Fish Internally mounted fuel manifold with support pins
US9068508B2 (en) * 2006-10-24 2015-06-30 Pratt & Whitney Canada Corp. Gas turbine internal manifold mounting arrangement
US20120186257A1 (en) * 2006-10-24 2012-07-26 Jason Fish Gas turbine internal manifold mounting arrangement
US8418468B2 (en) 2010-04-06 2013-04-16 General Electric Company Segmented annular ring-manifold quaternary fuel distributor
US8438852B2 (en) 2010-04-06 2013-05-14 General Electric Company Annular ring-manifold quaternary fuel distributor
US20130180253A1 (en) * 2012-01-13 2013-07-18 General Electric Company System and method for supplying a working fluid to a combustor
US9267436B2 (en) * 2013-03-18 2016-02-23 General Electric Company Fuel distribution manifold for a combustor of a gas turbine
US20150082770A1 (en) * 2013-09-20 2015-03-26 Mitsubishi Hitachi Power Systems, Ltd. Dual-Fuel Burning Gas Turbine Combustor
US10094567B2 (en) * 2013-09-20 2018-10-09 Mitsubishi Hitachi Power Systems, Ltd. Dual-fuel injector with a double pipe sleeve gaseus fuel flow path
US11156162B2 (en) * 2018-05-23 2021-10-26 General Electric Company Fluid manifold damper for gas turbine engine
CN114876646A (zh) * 2022-07-11 2022-08-09 成都中科翼能科技有限公司 一种燃气轮机燃油总管的支撑结构及燃油总管总成
CN114876646B (zh) * 2022-07-11 2022-09-30 成都中科翼能科技有限公司 一种燃气轮机燃油总管的支撑结构及燃油总管总成

Also Published As

Publication number Publication date
DE2202508C3 (de) 1981-06-04
FR2122308B1 (enrdf_load_stackoverflow) 1976-03-05
GB1329944A (en) 1973-09-12
DE2202508A1 (de) 1972-07-27
DE2202508B2 (de) 1980-07-10
FR2122308A1 (enrdf_load_stackoverflow) 1972-09-01

Similar Documents

Publication Publication Date Title
US3768251A (en) Fixing of fuel injection manifolds into combustion chambers
US6761035B1 (en) Thermally free fuel nozzle
JP2587576B2 (ja) ガスタービン用燃料ノズル組立体の製造方法、及び燃料ノズル組立体におけるノズルキャップの交換方法
US4592200A (en) Turbo-jet engine afterburner system
JP6695801B2 (ja) 可撓性支持構造体を備えた燃料ノズル
US3420058A (en) Combustor liners
JP5970466B2 (ja) パルスデトネーション燃焼器
US6679062B2 (en) Architecture for a combustion chamber made of ceramic matrix material
US20090260365A1 (en) Augmentor Spray Bar Mounting
JPH0236782B2 (enrdf_load_stackoverflow)
US7506514B2 (en) Augmentor fuel conduit bushing
JP2014173837A (ja) 複数の燃料噴射器を持つ多管式燃料ノズルを有するシステム及び方法
US3269116A (en) Centrally supported flameholder
JPH01244120A (ja) ガスタービンエンジン
US3315468A (en) Cooled flameholder assembly
US2979900A (en) Ducted fan flameholder
US7581398B2 (en) Purged flameholder fuel shield
US3465525A (en) Gas turbine bypass engines
US2847825A (en) Gas turbine thrust augmenter comprising water injection ring
GB2024403A (en) Flame-holder
US3295325A (en) Jet engine afterburner flameholder
JP2016532809A (ja) ノズルの固定部および可動部間に密封装置を備えたロケットエンジン用燃焼ガス噴出ノズル
US3910038A (en) Afterburner fuel injection devices for jet engines
US2988878A (en) Fuel nozzle for bypass engine
US3002352A (en) Flameholder construction