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EP0813670B1 - Chambre de combustion a anneau double et etagement axial pour une turbine a gaz - Google Patents

Chambre de combustion a anneau double et etagement axial pour une turbine a gaz Download PDF

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Publication number
EP0813670B1
EP0813670B1 EP96904099A EP96904099A EP0813670B1 EP 0813670 B1 EP0813670 B1 EP 0813670B1 EP 96904099 A EP96904099 A EP 96904099A EP 96904099 A EP96904099 A EP 96904099A EP 0813670 B1 EP0813670 B1 EP 0813670B1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
pilot burner
section
zone
burner zone
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
EP96904099A
Other languages
German (de)
English (en)
Other versions
EP0813670A1 (fr
Inventor
Norbert Brehm
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.)
Rolls Royce Deutschland Ltd and Co KG
Original Assignee
Rolls Royce Deutschland Ltd and Co KG
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
Priority claimed from DE1995108109 external-priority patent/DE19508109A1/de
Priority claimed from DE1996100837 external-priority patent/DE19600837A1/de
Application filed by Rolls Royce Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG
Publication of EP0813670A1 publication Critical patent/EP0813670A1/fr
Application granted granted Critical
Publication of EP0813670B1 publication Critical patent/EP0813670B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • F23R3/34—Feeding into different combustion zones

Definitions

  • the invention relates to an axially stepped annular combustion chamber of a gas turbine with a central axis, with a plurality of pilot burners located between annular wall sections and with main burners opening downstream and radially outside of this into the combustion chamber, to which a main burner zone adjoins, with an outer and an inner ring Combustion chamber wall, which each extend towards the combustion chamber outlet, the inner combustion chamber wall in the region of the pilot burner zone having a wall section running essentially parallel to the pilot burner axis.
  • the inner combustion chamber wall following the inner wall section forming the pilot burner zone and also essentially parallel to the central axis, runs towards the main burner zone with respect to the combustion chamber (ie viewed from within the combustion chamber) when viewed downstream has convex-concave deflection section, which, viewed in the radial direction with respect to the central axis, merges between the pilot burner axis and the downstream edge of the outer pilot burner wall section into a wall section which runs in a straight line and slightly diverging with respect to the central axis to the combustion chamber outlet.
  • Advantageous training and further education are included in the subclaims.
  • Fig. 1 is a partial longitudinal section of an annular combustion chamber is shown.
  • Fig. 2 shows two possible partial cross sections of an inventive Ring combustion chamber.
  • the central axis is a fundamentally known one Annular combustion chamber 2 in particular referred to an aircraft gas turbine.
  • the Annular combustion chamber 2 are several pilot burners distributed over their circumference 3 and several main burners 4 are arranged.
  • the main burner 4 are like usual in the radial direction outside and can in a preferred embodiment with their longitudinal axes or main burner axes 4a inclined with respect to the longitudinal axes 3a of the pilot burner 3, d. H. inclined towards the so-called pilot burner axes 3a.
  • the radial direction Main burners 4 arranged outside the pilot burner 3 thus open out downstream of the pilot burner 3 into the combustion chamber 2 Pilot burner 3 a so-called pilot burner zone 5, while directly downstream of the Main burner 4, a so-called main burner zone 5 'is formed.
  • the entire combustion chamber 2 i.e. the unit of pilot burner zone 5 and main burner zone 5 'from an outer annular combustion chamber wall 10 and towards the central axis 1 from an inner combustion chamber wall 11.
  • the latter consists of individual so-called wall sections, and from an inner wall section assigned to the pilot burner zone 5 6a, from an adjoining so-called deflection section 12, and from a wall section 13 leading to the combustion chamber outlet 8.
  • the pilot burner zone 5 is limited in the radial direction towards the outside from an outer wall section 6b which extends to the main burner 4.
  • the outer wall section 6b closes or closes the main burner (s) 4, whereby - as can be seen - each main burner 4 or each main burner axis 4a inclined to the pilot burner axis 3a each Pilot burner 3 is arranged. Downstream far outside of the combustion chamber would the two longitudinal axes 3a, 4a of the burners 3, 4 intersect while the longitudinal axis 3a is substantially parallel to the central axis 1 is aligned.
  • the individual Longitudinal axes 3a, 4a of the pilot burner 3 or the main burner 4 are different (for example, parallel) to be arranged.
  • the pilot burners also need to 3 and main burner 4 not - as shown here - each in one common longitudinal section plane, but it can be the pilot burner 3 and the main burner 4 also offset from one another in the circumferential direction be arranged, as shown in simplified form in FIG. Basically, the direction of flow is still generally in the combustion chamber 2 the combustion gases represented by arrow 7.
  • the course of the inner combustion chamber wall 11 is essential here points - as shown - to the one forming the pilot burner zone 5 Wall section 6a one running towards the main burner zone 5 ' Deflection section 12.
  • This deflection section 12 is at least partially in the radial direction (by definition this is perpendicular to the central axis 1) aligned, i.e. a straight extension of the deflection section 12 would center axis 1 in the embodiment shown here cut at an angle of approx. 45 °.
  • This partially radial alignment of the Deflection section 12 causes the combustion gases of the pilot burner 3 guided through this deflection section 12 essentially in a radial direction Enter the direction into the main burner zone 5 '.
  • This course of the inner combustion chamber wall 11 can also be described in such a way that this combustion chamber wall 11 in the region of the deflection section 12 and in relation to the combustion chamber 2, that is to say from the interior viewed from the combustion chamber when viewed downstream (namely in flow direction 7) is convex-concave.
  • the transition in terms of straight line the central axis 1 is slightly divergent to the combustion chamber outlet 8 Viewed in the radial direction, the wall section lies between the pilot burner axis 3a and the downstream edge of the outer Pilot burner wall section 6b.
  • This described design represents an optimal mix of the above Main burner 4 with fuel entering the main burner zone 5 ' the air in the main burner zone 5 '. This will reduce the exhaust emissions minimized and there can be the temperature distribution at the combustion chamber outlet 8 aligned to that of a non-stepped combustion chamber become.
  • the outer wall section 6b of the pilot burner zone 5 facing the main burner 4 is inclined relative to the longitudinal axis 3a of the associated pilot burner 3 in such a way that the cross section D of the pilot burner zone 5 is in the flow direction, ie from the pilot burner 3 in the direction of the arrow 7 to the center the combustion chamber 2 down.
  • the axially stepped according to the invention described here can be Ring combustion chamber 2 basically as an assembly of two independent Designate a non-stepped ring burner.
  • the main burner zone is on the outside 5 'constructed like a conventional non-staged ring combustion chamber, the main burner axis 4a essentially in the direction of the combustion chamber axis shows or coincides with this.
  • Mixed air jets 9 are in the main burner zone 5 'or in the ring combustion chamber 2 on both sides, i.e. admixed from the inside and outside, as is the case with conventional ones Annular combustion chambers is common. It is now also planned for this (conventional) ring combustion chamber 2 a coupled pilot burner zone 5, i.e. quasi a separate pilot combustion chamber, the radial inside and upstream to the main burner zone 5 '.
  • the described design of the annular combustion chamber advantageously results 2 additionally an extremely compact design, i.e. the Diameter of a ring combustion chamber designed in this way or its so-called. Overall height can be minimized. This results in the cheapest Ratios when the dimension of the penetration depth A is related to the cross section D * of the pilot burner zone 5 in the area of the pilot burner 3 in the value range from 0.1 to 0.3, i.e. 0.1 ⁇ ⁇ / D * ⁇ 0.3.
  • the outer wall section 6b of the pilot burner zone 5 also runs as the entire ring combustion chamber 2 is essentially ring-shaped, however this does not mean that the reduction in cross section mentioned above Pilot burner zone 5 essentially over the entire ring combustion chamber 2 must be provided in the same size all around, although this is quite possible. Rather, only in the area of the main burner 4 quasi bowl-shaped depressions otherwise essentially parallel to the pilot burner longitudinal axis 3 extending outer wall section 6b be provided.
  • the latter design is in the lower half of Fig.2 shown schematically, while the first design in the upper half of Fig.2, which is basically a view against the flow direction 7 shows.
  • pilot burner zone 5 formed by cup-shaped depressions
  • Cross-sectional reduction of the pilot burner zone 5 essentially in the through the longitudinal axes 4a of the main burner 4 and the central axis 1 of the Ring combustion chamber 2 levels provided.
  • the Wall section 13 essentially part of the main burner zone 5 ' or the corresponding main combustion chamber.
  • the pilot burner zone 5 viewed in the direction of flow 7 in the region of the deflection section 12 their end.
  • Mixed air jets 14 both inside and - shortly upstream of the main burner 4 - are supplied on the outside.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)

Claims (8)

  1. Chambre de combustion annulaire étagée axialement de turbine à gaz ayant un axe central (1), plusieurs brûleurs pilotes (3) situés entre des segments de paroi annulaires (6a, 6b) et en aval et radialement à l'extérieur de ceux-ci, des brûleurs principaux (4) débouchant dans la chambre de combustion (2), suivie d'une zone de combustion principale (5') avec une paroi de chambre de combustion annulaire respective extérieure (10) et intérieure (11), qui s'étend chaque fois vers la sortie (8) de la chambre de combustion, la paroi intérieure (11) de la chambre de combustion ayant au niveau de la zone (5) des brûleurs principaux, un segment de paroi (6a) essentiellement parallèle à l'axe parallèle (3a) des brûleurs pilotes,
    caractérisée en ce que
    la paroi intérieure (11) de la chambre de combustion présente à la suite du segment de paroi (6a) formant la zone (5) des brûleurs pilotes et qui est essentiellement parallèle à l'axe central (1), un segment de déviation (12) de forme convexe, concave lorsqu'on regarde dans la direction aval, par rapport à la zone (5') des brûleurs principaux, en se référant à la chambre de combustion (2), ce segment de déviation étant dirigé dans la direction radiale par rapport à l'axe central (2), entre l'axe (3a) des brûleurs pilotes et l'arête aval du segment de paroi (6b) extérieur des brûleurs pilotes, en rejoignant un segment de paroi (13) qui correspond à une ligne droite et diverge légèrement par rapport à l'axe central (1), vers la sortie (8) de la chambre de combustion.
  2. Chambre de combustion interne annulaire selon la revendication 1,
    caractérisée en ce que
    les gaz de combustion des brûleurs pilotes (3) arrivent en étant conduits par le segment de déviation (12) essentiellement dans la direction radiale dans la zone (5') des brûleurs principaux.
  3. Chambre de combustion interne annulaire selon les revendications 1 ou 2,
    caractérisée en ce que
    le segment de paroi extérieur (6b) de la zone de brûleurs pilotes (5) tournée les brûleurs principaux (4), est incliné par rapport à l'axe longitudinal (3a) du brûleur pilote associé (3), pour diminuer la section (D) de la zone de brûleurs pilotes (5) dans la direction d'écoulement (7).
  4. Chambre de combustion interne annulaire selon la revendication 3,
    caractérisée en ce que
    le degré de réduction de section de la zone (5) des brûleurs pilotes qui s'établit par la profondeur de pénétration (Δ) des brûleurs principaux (4) dans la zone (5) des brûleurs pilotes rapportée à la section (D*) de la zone (5) des brûleurs pilotes se situe dans la zone des brûleurs pilotes (3) dans la plage des valeurs comprises entre 0,1 et 0,3.
  5. Chambre de combustion interne annulaire selon la revendication 3 ou 4,
    caractérisée en ce que
    la réduction de section de la zone (5) des brûleurs pilotes est prévue essentiellement dans des plans passant par l'axe longitudinal (4a) des brûleurs principaux (4) et l'axe central (1) de la chambre de combustion annulaire (2).
  6. Chambre de combustion interne annulaire selon la revendication 3 ou 4,
    caractérisée en ce que
    la réduction de section de la zone (5) des brûleurs pilotes est prévue essentiellement de manière périphérique pour toute la chambre de combustion annulaire (2).
  7. Chambre de combustion interne annulaire selon l'une quelconque des revendications précédentes,
    caractérisée en ce que
    les brûleurs principaux (4) et les brûleurs pilotes (5) sont décalés dans la direction périphérique.
  8. Chambre de combustion interne annulaire selon l'une quelconque des revendications précédentes,
    caractérisée en ce que
    l'extrémité aval de la zone des brûleurs pilotes (5) est définie par des jets d'air mélangés (14) arrivant par des ouvertures prévues dans la paroi de la chambre de combustion (11, 6b).
EP96904099A 1995-03-08 1996-03-04 Chambre de combustion a anneau double et etagement axial pour une turbine a gaz Expired - Lifetime EP0813670B1 (fr)

Applications Claiming Priority (5)

Application Number Priority Date Filing Date Title
DE1995108109 DE19508109A1 (de) 1995-03-08 1995-03-08 Axial gestufte Ring-Brennkammer einer Gasturbine
DE19508109 1995-03-08
DE19600837 1996-01-12
DE1996100837 DE19600837A1 (de) 1996-01-12 1996-01-12 Axial gestufte Ring-Brennkammer einer Gasturbine
PCT/EP1996/000895 WO1996027766A1 (fr) 1995-03-08 1996-03-04 Chambre de combustion a anneau double et etagement axial pour une turbine a gaz

Publications (2)

Publication Number Publication Date
EP0813670A1 EP0813670A1 (fr) 1997-12-29
EP0813670B1 true EP0813670B1 (fr) 2000-06-28

Family

ID=26013126

Family Applications (1)

Application Number Title Priority Date Filing Date
EP96904099A Expired - Lifetime EP0813670B1 (fr) 1995-03-08 1996-03-04 Chambre de combustion a anneau double et etagement axial pour une turbine a gaz

Country Status (5)

Country Link
US (1) US6058710A (fr)
EP (1) EP0813670B1 (fr)
CA (1) CA2216115A1 (fr)
DE (1) DE59605505D1 (fr)
WO (1) WO1996027766A1 (fr)

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DE102008053755A1 (de) 2008-10-28 2010-04-29 Pfeifer, Uwe, Dr. Register Pilotbrennersystem für Gasturbinen
US8281597B2 (en) * 2008-12-31 2012-10-09 General Electric Company Cooled flameholder swirl cup
RU2534189C2 (ru) * 2010-02-16 2014-11-27 Дженерал Электрик Компани Камера сгорания для газовой турбины(варианты) и способ эксплуатации газовой турбины
EP2434222B1 (fr) * 2010-09-24 2019-02-27 Ansaldo Energia IP UK Limited Méthode d'opération d'une chambre de combustion
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US10739003B2 (en) 2016-10-03 2020-08-11 United Technologies Corporation Radial fuel shifting and biasing in an axial staged combustor for a gas turbine engine
US10508811B2 (en) 2016-10-03 2019-12-17 United Technologies Corporation Circumferential fuel shifting and biasing in an axial staged combustor for a gas turbine engine
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Also Published As

Publication number Publication date
WO1996027766A1 (fr) 1996-09-12
US6058710A (en) 2000-05-09
CA2216115A1 (fr) 1996-09-12
DE59605505D1 (de) 2000-08-03
EP0813670A1 (fr) 1997-12-29

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