EP0743490B1 - Brennkammer mit einer Vielzahl von Filmkühlungsbohrungen die in verschiedene axiale und tangentiale Richtungen geneigt sind - Google Patents

Brennkammer mit einer Vielzahl von Filmkühlungsbohrungen die in verschiedene axiale und tangentiale Richtungen geneigt sind Download PDF

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Publication number
EP0743490B1
EP0743490B1 EP96400863A EP96400863A EP0743490B1 EP 0743490 B1 EP0743490 B1 EP 0743490B1 EP 96400863 A EP96400863 A EP 96400863A EP 96400863 A EP96400863 A EP 96400863A EP 0743490 B1 EP0743490 B1 EP 0743490B1
Authority
EP
European Patent Office
Prior art keywords
orifices
zones
wall
axial
angle
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
EP96400863A
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English (en)
French (fr)
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EP0743490A1 (de
Inventor
Denis Roger Henri Ansart
Patrick Samuel André Ciccia
Michel André Albert Desaulty
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
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
SNECMA SAS
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Publication date
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Publication of EP0743490A1 publication Critical patent/EP0743490A1/de
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Publication of EP0743490B1 publication Critical patent/EP0743490B1/de
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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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/06—Arrangement of apertures along the flame tube
    • 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
    • F23R3/002—Wall structures
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2250/00—Geometry
    • F05B2250/30—Arrangement of components
    • F05B2250/32—Arrangement of components according to their shape
    • F05B2250/322—Arrangement of components according to their shape tangential
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2260/00—Function
    • F05B2260/20—Heat transfer, e.g. cooling
    • F05B2260/202—Heat transfer, e.g. cooling by film cooling

Definitions

  • the present invention relates to a combustion chamber, in particular of a turbomachine, which is delimited by at least one wall axial provided with a plurality of through holes constituting a "multi-perforation" intended, in particular, for the passage of a refrigeration of said axial wall, and provided with a plurality of holes for dilution regularly distributed in a transverse plane compared to the general direction of the flow of burnt gases from the combustion, each orifice having a geometric axis inclined at an angle A relative to the normal to said wall, said genometric axis being arranged in a plane containing said normal which makes an angle B by relation to the plan defined by said normal and the general direction flue gas flow.
  • the cooling mode by multiperforation is known.
  • the orifices are generally staggered with a network of equidistant meshes.
  • EP-A-0 486 133 discloses a wall of this type, in which the orifices are inclined in axial planes.
  • EP-A-0 492 864 further reveals that the orifices are also inclined by a tangential angle B which generally coincides with the angle of the flue gas vortex along the internal surface of the wall.
  • EP-A-0 592 161 shows in FIG. 6 an annular wall multi-perforated combustion chamber in which the orifices are defined by an axial inclination A and a tangential angle B of in such a way that the flow of fresh air introduced into the room creates a protective crown of air which swirls around the flow of burnt gases.
  • 3D calculations show that the flow of gases in the combustion chamber is not always longitudinal, but only in some areas it is slightly tilted or even opposed to flow, especially downstream of the dilution holes. It can be produce detachments of cooling air in these areas.
  • the purpose of the present invention is to prevent the air from the multiperforation does not take off from the wall.
  • the present invention therefore proposes to locally orient the orifices according to the local flow of the burnt gases.
  • the wall is subdivided into several zones, in each of which the orifices are defined by inclinations A and angles B respectively having identical values and calculated as a function characteristics of the flue gas flow in each of said zones.
  • said wall is subdivided in particular into first zones located respectively downstream of the dilution holes, and in which the orifices are directed against the current of the general direction of the flue gas flow, second and third zones arranged on either side of said first zones with respect to axial planes passing through the corresponding dilution holes, and a fourth zone covering the rest of said wall.
  • the holes in the fourth zone have an inclination axial greater than 30. Their angle B is substantially equal to 0 °. The flow of fresh air from these holes licks the surface internal wall in the direction of the axial flow of the burnt gases.
  • the orifices made in the first zones diffuse a cooling air against the current of the general direction of flue gas flow.
  • Their tilt A is between 0 ° and -60 °, and their angle B is substantially equal to 0 °.
  • a second and a third zone are provided, of which the orifices diffuse cooling air towards the passing axial plane through the corresponding dilution hole and in the direction of the general flow of burnt gases.
  • the combustion chamber 1 of annular type, has a outer annular axial wall 2 and an annular axial wall interior 3, joined at their upstream ends by a chamber bottom 4 equipped with injection systems 5, and having between their ends downstream an annular opening 6 for the exhaust of the burnt gases G towards a turbine not shown in the drawings.
  • the burnt gases G circulate in the internal cavity 7 of the combustion chamber 1 according to an axial general direction represented by the arrow D.
  • outer 2 and inner 3 axial walls define with the outer casings 8 and inner 9 of the annular passages 10 and 11 in which circulates cooling air A coming from a compressor not shown in the drawings and located upstream of the combustion 1.
  • the two walls 2 and 3 are provided with a plurality of holes for dilution 12 regularly distributed in an axial plane 13 perpendicular to the axis of the turbomachine, and a plurality of through holes 14 constituting a multi-perforation.
  • Part of the cooling air A enters axially into the internal cavity 7 through the dilution holes 12 and participates in depletion and cooling of the combustion gases in the dilution zone of combustion chamber 1, while the rest of air A enters the internal cavity 7 through the orifices 14 in order to form a cooling film on internal faces 2a and 3a of the walls axial 2 and 3.
  • Figure 2 shows the gas velocity diagram at vicinity of the internal face 2a of the external wall 2, in the region of two dilution holes 12a and 12b, this diagram having been obtained by 3D calculations.
  • This diagram shows that in zone 15 which separates the two dilution holes 12a and 12b, the gases flow in the direction D.
  • zones 16 located immediately downstream of the dilution 12a and 12b the gases flow on the contrary towards the holes of dilution 12a and 12b, i.e. in a direction globally opposite to direction D.
  • each zone 16 On either side of each zone 16, the gases flow in a direction inclined towards the axial plane 18 passing through the dilution hole corresponding, and generally directed in the direction of flow general of burnt gases D.
  • the burnt gases circulate according to direction D.
  • the 3D temperature diagram in the vicinity of the dilution also shows significant differences depending on the area.
  • the region of the wall 2 is subdivided and 3 which comprises the orifices 14 in several zones, in each of which, the angles of inclination A of the axes 30 of the orifices 14 by compared to the normal 31 to the wall are identical as well as the angles B planes 32 containing said axes 30 and the normals 31 relative to to the axial planes 33 containing said normal.
  • FIG 3 there is shown an axial wall portion 34 comprising two dilution holes 12a and 12b.
  • the arrow D represents the general direction of the flue gas flow in the combustion 1.
  • References 16a and 16b represent first zones in which the burnt gases flow against the current.
  • the burnt gases In the second zones 17a and 17b situated to the left of the axial planes 18a and 18b, the burnt gases generally flow in the direction of the arrows 19.
  • the gases In the third zones 19a and 19b located to the right of axial plane 18a and 18b, the gases flow in the direction of the arrows 20.
  • the gases flow generally in the direction of the arrow D.
  • the orifices 14 formed in the fourth zone 21 are defined by an inclination A 4 greater than 30 ° and an angle B substantially equal to 0 °.
  • the cooling air diffused by these orifices 14 enters the combustion chamber 1, in the general flow direction D of the gases, but with an inclination A 4 .
  • the orifices 14 formed in the first zone 16a are inclined so as to allow a diffusion of cooling air against the current of the general direction D.
  • the axes 30 of these orifices 14 form an angle A 1 with the normals 31 which is between -60 ° and 0 °.
  • the axes 30 of these orifices 14 are also parallel to the axial plane 18a passing through the axis 35 of the dilution hole 12a.
  • FIG 5 there is shown a small part 36 of the outer wall 2 at a third area 19b.
  • the orifices are drilled at an inclination A 3 relative to the normal 31 and in a plane making an angle B 3 with respect to the direction of the main flow D.
  • the angle B 3 is calculated in function of the average direction of local gas flow in the third zone 19b.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (6)

  1. Brennkammer, insbesondere für Turbomaschinen, die durch mindestens eine axiale Wand (2, 3) begrenzt wird, die mit mehreren durchgehenden Bohrungen (14) versehen ist, die eine "Multiperforation" darstellen, die insbesondere für den Durchgang eines Kühlungsfluids (A) für diese axiale Wand (2, 3) bestimmt ist, sowie mit mehreren Verdünnungslöchern (12) versehen ist, die in einer Querebene (13) zur allgemeinen Strömungsrichtung (D) der von der Verbrennung kommenden verbrannten Gase (G) liegt, gleichmäßig verteilt angeordnet sind, wobei die Geometrieachse (30) jeder Bohrung (14) um einen Winkel A zu der Normalen (31) der genannten Wand (2, 3) geneigt ist, wobei die genannte Geometrieachse (30) in einer Ebene (32) angeordnet ist, in der die genannte Normale (31) liegt und die einen Winkel B zu der Ebene (33) bildet, die durch die genannte Normale und die allgemeine Strömungsrichtung (D) der verbrannten Gase definiert wird, wobei die Wand (2, 3) in mehrere Zonen (16a, 16b, 17a, 17b, 19a, 19b, 21) unterteilt wird und in jeder von ihnen die Bohrungen (14) durch Neigungen A und Winkel B definiert sind, die jeweils identische Werte haben, die abhängig von der lokalen Strömung der verbrannten Gase (G) in jeder der genannten Zonen berechnet werden,
       dadurch gekennzeichnet, daß die genannte Wand (2, 3) in erste Zonen (16a, 16b), die sich jeweils hinter den Verdünnungslöchern (12a, 12b) befinden und in denen die Bohrungen (14) gegen die allgemeine Strömungsrichtung (D) der verbrannten Gase (G) gerichtet sind, in zweite und dritte Zonen (17a, 17b, 19a, 19b), die, bezogen auf die axialen Ebenen (18a, 18b) durch die entsprechenden Verdünnungslöcher (12a, 12b), beiderseits der genannten ersten Zonen (16a, 16b) angeordnet werden, und in eine vierte Zone (21), die den Rest der genannten Wand (2, 3) ausmacht, unterteilt wird.
  2. Brennkammer nach Anspruch 1, dadurch gekennzeichnet, daß die in der vierten Zone (21) ausgeführten Bohrungen (14) durch eine Neigung A von mehr als 30° definiert sind.
  3. Brennkammer nach Anspruch 2, dadurch gekennzeichnet, daß die in der vierten Zone (21) ausgeführten Bohrungen (14) durch einen Winkel B von im wesentlichen gleich 0° definiert sind.
  4. Brennkammer nach Anspruch 1, dadurch gekennzeichnet, daß die in den ersten Zonen (16a, 16b) ausgeführten Bohrungen (14) durch eine Neigung A definiert sind, die zwischen 0° und -60° liegt.
  5. Brennkammer nach Anspruch 4, dadurch gekennzeichnet, daß die in den ersten Zonen (16a, 16b) ausgeführten Bohrungen (14) durch einen Winkel B von im wesentlichen gleich 0° definiert sind.
  6. Brennkammer nach Anspruch 2, dadurch gekennzeichnet, daß die in den zweiten Zonen (17a, 17b) ausgeführten Bohrungen (14) durch Winkel B definiert sind, die entgegengesetzte Werte zu den Winkeln B haben, die die Bohrungen (14) in den dritten Zonen (19a, 19b) definieren.
EP96400863A 1995-04-26 1996-04-24 Brennkammer mit einer Vielzahl von Filmkühlungsbohrungen die in verschiedene axiale und tangentiale Richtungen geneigt sind Expired - Lifetime EP0743490B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9504968A FR2733582B1 (fr) 1995-04-26 1995-04-26 Chambre de combustion comportant une multiperforation d'inclinaison axiale et tangentielle variable
FR9504968 1995-04-26

Publications (2)

Publication Number Publication Date
EP0743490A1 EP0743490A1 (de) 1996-11-20
EP0743490B1 true EP0743490B1 (de) 1999-06-09

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EP96400863A Expired - Lifetime EP0743490B1 (de) 1995-04-26 1996-04-24 Brennkammer mit einer Vielzahl von Filmkühlungsbohrungen die in verschiedene axiale und tangentiale Richtungen geneigt sind

Country Status (5)

Country Link
US (1) US5775108A (de)
EP (1) EP0743490B1 (de)
JP (1) JP3302559B2 (de)
DE (1) DE69602804T2 (de)
FR (1) FR2733582B1 (de)

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Also Published As

Publication number Publication date
DE69602804D1 (de) 1999-07-15
JPH08312960A (ja) 1996-11-26
FR2733582B1 (fr) 1997-06-06
DE69602804T2 (de) 2000-01-27
EP0743490A1 (de) 1996-11-20
US5775108A (en) 1998-07-07
FR2733582A1 (fr) 1996-10-31
JP3302559B2 (ja) 2002-07-15

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