EP1636526A1 - Chambre a combustion - Google Patents

Chambre a combustion

Info

Publication number
EP1636526A1
EP1636526A1 EP04729621A EP04729621A EP1636526A1 EP 1636526 A1 EP1636526 A1 EP 1636526A1 EP 04729621 A EP04729621 A EP 04729621A EP 04729621 A EP04729621 A EP 04729621A EP 1636526 A1 EP1636526 A1 EP 1636526A1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
flow
heat shield
coolant
wall
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.)
Granted
Application number
EP04729621A
Other languages
German (de)
English (en)
Other versions
EP1636526B1 (fr
Inventor
Michael Huth
Peter Tiemann
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.)
Siemens AG
Original Assignee
Siemens AG
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 Siemens AG filed Critical Siemens AG
Priority to EP04729621.5A priority Critical patent/EP1636526B1/fr
Publication of EP1636526A1 publication Critical patent/EP1636526A1/fr
Application granted granted Critical
Publication of EP1636526B1 publication Critical patent/EP1636526B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

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
    • F23R3/005—Combined with pressure or heat exchangers

Definitions

  • the invention relates to a combustion chamber for a gas turbine, the combustion chamber wall of which is provided on the inside with a lining formed by a number of heat shield elements, the or each heat shield element forming an interior space which can be acted upon by a coolant.
  • the invention further relates to a gas turbine with such a combustion chamber.
  • Combustion chambers are part of gas turbines, which are used in many areas to drive generators or work machines. The energy content becomes one
  • Fuel used to generate a rotational movement of a turbine shaft is burned by burners in the combustion chambers connected downstream of them, compressed air being supplied by an air compressor.
  • the combustion of the fuel creates a working medium under high pressure at a high temperature.
  • This working medium is fed into a turbine unit downstream of the combustion chambers, where it relaxes in a cooperative manner.
  • Each burner can be assigned a separate combustion chamber, the working medium flowing out of the combustion chambers being able to be brought together in front of or in the turbine unit.
  • the combustion chamber can also be designed in a so-called annular combustion chamber design, in which a plurality, in particular all, of the burners open into a common, usually annular combustion chamber.
  • the components and components exposed to this medium are exposed to high thermal loads.
  • the aim is usually to achieve the most uniform possible cooling of the components.
  • the combustion chamber wall is to page usually on its interior lined with heat shield elements, which can be provided with a particularly heat-resistant 'protective layers, and that are cooled by the actual combustion chamber wall.
  • a cooling method also known as "impingement cooling”
  • impingement cooling a coolant, usually cooling air, is supplied to the heat shield elements through a large number of bores in the combustion chamber wall, so that the coolant is essentially perpendicular to the combustion chamber wall.
  • the coolant that is heated up by the cooling process for example cooling air, is then discharged from the interior space that the combustion chamber wall forms with the heat shield elements so-called convective cooling is used.
  • the invention is based on the object of specifying a combustion chamber of the type mentioned above which, with a comparatively simple construction, is suitable for a particularly high system efficiency and at the same time the areas exposed to high temperatures can be effectively cooled. Furthermore, a gas turbine with the above-mentioned combustion chamber is to be specified.
  • this object is achieved according to the invention by a combustion chamber for a gas turbine, the combustion chamber wall of which is provided on the inside with a lining formed by a number of heat shield elements, the or each heat shield element forming a coolant-containing interior with the combustion chamber wall, in which a flow element is inserted for the targeted setting of a coolant flow.
  • the invention is based on the knowledge that after a structural design of a combustion chamber has been carried out, the geometry of the interior formed for cooling purposes is defined.
  • the interior space provided for this purpose is filled and flowed through substantially uniformly. It is not possible to adapt the cooling capacity to the actual local coolant requirement of a heat shield element. For this reason, the action on the interior for cooling the heat shield element is quite unspecific, since it cannot be adapted sufficiently flexibly to the respective actual local cooling requirements. Heat dissipation from the interior can be set within certain limits only by the total amount of coolant supplied to the intermediate space per time.
  • the invention shows for the first time a new way of adapting the cooling capacity to the local requirements in the interior.
  • a flow element By inserting a flow element, even after the combustion chamber has been designed, with defined geometry of the interior - an operational cooling adjustment possible.
  • the flow element in the interior acts directly on the coolant flow in the interior and leads to its targeted adjustment with regard to strength and flow direction such that the heat shield element can be cooled as required. This increases the cooling efficiency.
  • a flow channel for coolant is formed by the flow element, in which the flow speed of the coolant flow is increased compared to the flow speed upstream of the flow element.
  • the flow element arranged in the interior accordingly leads to a local increase in the flow rate of coolant in the flow channel. Accordingly, the increased flow rate locally results in increased heat transfer from the thermally highly stressed heat shield element to the coolant, for example cooling air.
  • the flow channel is advantageously delimited directly by a wall of the heat shield element to be cooled. The heat transfer into the coolant and the heat removal is favored by the increased flow rate.
  • the flow velocity is increased, for example, by locally reducing the flow cross section through the flow element in the interior.
  • a heat shield element is preferably assigned a respective flow element for cooling a thermally highly stressed wall section of the heat shield element. This ensures an individual, targeted setting of the coolant flow for each heat shield element for cooling, depending on the requirement.
  • the arrangement and the structural design of the flow element for cooling adaptation of a heat shield element is such that the flow channel for coolant thus formed supplies a wall section with increased temperature load during operation of the combustion chamber with coolant. Due to the increased speed in the flow channel, this wall section in particular is cooled more. In other wall sections, however, this is not necessary and a reduced flow speed is sufficient.
  • the heat shield element which can be cooled in this way can have a longitudinal axis and a transverse axis and comprises a wall with a hot side which has a hot side surface which can be acted upon by a hot medium, for example hot combustion gas, and a cold side opposite the hot side.
  • the cold side is the side of the heat shield element facing the combustion chamber and delimits the interior.
  • the heat shield element can comprise a first wall section and a second wall section adjoining the first wall section along a longitudinal axis.
  • the side of the heat shield element facing the interior forms a cold side of the wall sections to which the coolant is applied for cooling purposes.
  • the second wall section can be inclined towards the hot side in relation to the first wall section. Depending on the angle of inclination, different installation or operating situations of the heat shield element can thus be realized.
  • the heat shield element can be used as a segment of the gas turbine liner.
  • a large number of such heat shield elements can be used to cover the entire combustion chamber wall of the ring combustion chamber over the entire circumference of the ring combustion chamber.
  • the hot gas flow from the burner outlet must be deflected by an angle in the direction of the turbine.
  • the combustion chamber liner is provided for this deflection purpose. With a combustion chamber liner, which has one or more locally selectable heat shield elements, this is possible in a particularly simple manner.
  • the first wall section which faces the burner outlet and is directly exposed to the hot combustion gas on the hot side, requires an increased cooling capacity in order to ensure safe operation of the combustion chamber. With the invention, however, targeted cooling of this thermally highly stressed wall section of the heat shield element is guaranteed.
  • a heat shield element with an associated flow element is therefore particularly suitable for a heat-resistant combustion chamber lining, since the deflection angle and the local cooling power requirement can be adjusted to the respective circumstances due to the first and the second wall section inclined relative to it.
  • a particularly advantageous inflow of the hot gases generated by the combustion process into a turbine downstream of the combustion chamber can also be achieved.
  • the heat shield element is preferably designed as a single-shell hollow body, which hollow body has a cavity in which the flow element is arranged. This structural configuration enables the flow element to be inserted and accommodated safely when the combustion chamber is being assembled or when a combustion chamber is retrofitted with a flow element for cooling adaptation. Furthermore, the flow element is protected against exposure to hot gas, since it is located in the cavity which is closed on the hot side.
  • the flow element is designed accordingly for the most efficient and adapted cooling and is placed in the cavity in such a way that high flow speeds result in the thermally highly stressed wall sections.
  • the half-shell of the single-shell hollow body is aligned with the open side in the direction of the combustion chamber wall, so that the cavity also forms a subspace of the interior which is acted upon with coolant for cooling purposes.
  • the flow element is positively attached to the combustion chamber wall.
  • the positive connection leads to an arrangement of the heat shield element, flow element and combustion chamber wall that is mechanically not particularly sensitive to vibrations. Furthermore, the positive connection between the combustion chamber wall and
  • Flow element assembly and enables a precise attachment of the flow element in a predetermined position, so that the flow element can perform the desired cooling task in the interior.
  • the heat input into the coolant for the actual energy conversion process in the combustion chamber is advantageously recovered.
  • the cooling air heated during the combustion chamber cooling and used as coolant in the interior is advantageously fed into the combustion chamber, the preheated cooling air being the exclusive before or additional combustion air can serve.
  • the interior in order to supply the outflowing coolant to the combustion process in the combustion chamber, the interior is fluidically preferably connected on the outlet side to a collecting space, which in turn is connected upstream of the combustion chamber on the air side.
  • the heated coolant can be mixed with the rest of the compressor mass flow via a throttle device and fed to the combustion process, so that closed air cooling is achieved.
  • the flow element is preferably detachably connected to the combustion chamber wall for the targeted adjustment of the coolant flow in the interior.
  • the connection can e.g. be achieved by a screw connection, the attachment of the flow element from the outside through the combustion chamber wall or from the inside, i.e. is done inside.
  • the connection can also be achieved by hooking.
  • the heat shield element and the combustion chamber wall have corresponding connections or to achieve a detachable connection. Fasteners on.
  • the flow element is further preferably made of metal, in particular a metal sheet or a metal plate or a metallic molded part, e.g. a casting.
  • the above-mentioned combustion chamber is preferably part of a gas turbine.
  • 2 shows a section through a combustion chamber
  • 3 shows a sectional view of a section of the combustion chamber in the region of the combustion chamber wall with a flow element
  • FIG. 4 shows a sectional view of a section of the combustion chamber with the flow element modified compared to FIG. 3,
  • FIG. 6 shows a view of the heat shield element shown in FIG. 5 along its longitudinal axis on the end face
  • FIG. 7 shows a perspective exploded view of a section of a combustion chamber wall with a heat shield element and with a flow element.
  • the gas turbine 1 has a compressor 2 for combustion air, a combustion chamber 4 and a turbine 6 for driving the compressor 2 and a generator or a working machine (not shown).
  • the turbine 6 and the compressor 2 are arranged on a common turbine shaft 8, also referred to as a turbine rotor, to which the generator or the working machine is also connected, and which is rotatably mounted about its central axis 9.
  • the combustion chamber 4, which is designed as an annular combustion chamber, is equipped with a number of burners 10 for the combustion of a liquid or gaseous fuel.
  • the turbine 6 has a number of rotatable rotor blades 12 connected to the turbine shaft 8.
  • the blades 12 are arranged in a ring shape on the turbine shaft 8 and thus form a number of rows of blades.
  • the turbine 6 comprises a number of fixed guide vanes 14, which are also attached to an inner casing 16 of the turbine 6 in a ring shape, with the formation of rows of guide vanes.
  • the blades 12 are used to drive the turbine shaft 8 by transmitting momentum from the hot medium flowing through the turbine 6, the working medium M.
  • the guide blades 14, serve to guide the flow of the working medium M between two successive rows of blades or rotor blades as seen in the flow direction of the working medium M.
  • a successive pair of a ring of guide vanes 14 or a row of guide blades and a ring of rotor blades 12 or a row of rotor blades is also referred to as a turbine stage.
  • Each guide vane 14 has a platform 18, also referred to as a blade root, which is arranged as a wall element for fixing the respective guide vane 14 to the inner housing 16 of the turbine 6.
  • the platform 18 is a thermally comparatively heavily loaded component, which forms the outer boundary of a heating gas channel for the working medium M flowing through the turbine 6.
  • Each rotor blade 12 is fastened in an analogous manner to the turbine shaft 8 via a platform 20 which is also referred to as a blade root.
  • a guide ring 21 is arranged on the inner casing 16 of the turbine 6 between the spaced-apart platforms 18 of the guide vanes 14 of two adjacent rows of guide vanes.
  • the outer surface of each guide ring 21 is also exposed to the hot working medium M flowing through the turbine 6 and is spaced in the radial direction from the outer end 22 of the rotor blade 12 lying opposite it by a gap.
  • the guide rings 21 arranged between adjacent rows of guide vanes serve in particular as cover elements which protect the inner wall 16 or other housing installation parts from thermal ones Overload by the hot working medium M flowing through the turbine 6 protects.
  • the combustion chamber 4 is delimited by a combustion chamber housing 29, a combustion chamber wall 24 being formed on the combustion chamber side.
  • the combustion chamber 4 is designed as a so-called annular combustion chamber, in which a plurality of burners 10 arranged in the circumferential direction around the turbine shaft 8 open into a common annular combustion chamber space.
  • the combustion chamber 4 is configured in its entirety as a corresponding ring-shaped structure which is positioned around the turbine shaft 8.
  • the combustion chamber 4 is shown in section in FIG. 2, which continues like a torus around the turbine shaft 8.
  • the combustion chamber 4 has an initial or inflow section into which the outlet of the respectively associated burner 10 opens.
  • the cross section of the combustion chamber 4 then narrows, the resulting flow profile of the working medium M being taken into account in this area.
  • the combustion chamber 4 has a curvature in longitudinal section through which the working medium M flows out of the
  • Combustion chamber 4 is favored in a first rotor blade row, which is downstream for a particularly high impulse and energy transfer, as seen on the flow side.
  • the working medium M When flowing through the combustion chamber, the working medium M is deflected from a direction essentially parallel to the burner axis 39 into a direction parallel to the central axis 9.
  • the combustion chamber 4 is designed for a comparatively high temperature of the working medium M of approximately 1200 ° C. to 1500 ° C.
  • the combustion chamber wall 24 is provided on its side facing the working medium M with a combustion chamber lining formed from heat shield elements 26.
  • the heat shield elements 26 are fastened to the combustion chamber wall 24 via fastening means 37, leaving a gap, the gap dimension of which at the same time corresponds to the dimension of the interior 27 perpendicular to the combustion chamber wall 24.
  • Each heat shield element 26 is equipped with a particularly heat-resistant protective layer 31 on the working medium side, that is to say on its hot side 35.
  • a cooling system is also provided for the heat shield elements 26.
  • the cooling system is based on the principle of convective cooling, in which coolant, for example cooling air, is guided along a surface of the component to be cooled.
  • the cooling system can be designed for impingement cooling, in which cooling air is blown as coolant K under sufficiently high pressure at a large number of points onto the component to be cooled, perpendicular to a component surface.
  • the cooling system is designed for a reliable, area-wide application of cooling air K to the heat shield elements 26 and also for a particularly low loss of coolant pressure.
  • the heat shield elements 26 are cooled from their cold side 33 by the cooling air K, which is supplied to an intermediate space 27 formed between the heat shield element 26 and the combustion chamber wall 24 by suitable supply lines (not shown in more detail) and, depending on the cooling mechanism, on or along the cold side 33 of a respective heat shield element 26 is passed.
  • the closed air cooling thus enables higher performance / efficiency and low lower NO x emissions than, for example, open air cooling.
  • open air cooling the cold "cooling air is mixed with the heating gas flow downstream of the combustion, which leads to lower gas turbine efficiency and higher pollutant values.
  • combustion chamber liner For a temperature-resistant as well as vibration-resistant construction of the combustion chamber 4 designed as an annular combustion chamber, a combustion chamber lining with a number of temperature-resistant and dimensionally stiffened heat-shielding elements 26 is provided. In this way, a complete, largely leak-free combustion chamber lining is formed in the annular space, a so-called combustion chamber liner.
  • a flow element 49 is inserted in the interior space 27 formed between the heat shield element 26 and the combustion chamber wall 24. This is positively attached to the combustion chamber wall 24, e.g. by means of a suitable hook or screw connection.
  • the flow element 49 is arranged in such a way that a thermally highly stressed first wall section 47A of the heat shield element 26, as shown here in the vicinity of the burner 10, can be cooled more intensely.
  • the flow element 49 effects in the interior 27 a flow channel 51 for the coolant K with upstream of the flow element 49, that is in the area of the opposite to the first
  • Wall section 47A less thermally stressed wall section 47B, reduced flow cross section. This leads to a selectively adjustable local increase in the flow rate of the coolant in the flow channel 51 and thus to an increased heat transfer from the thermally highly stressed wall section 47A to the coolant K.
  • the positive flow elements 49 on the combustion chamber wall 24 can advantageously also be attached to the combustion chamber wall 24 from the outside through the housing 29 or from the inside in the course of a revision measure of an already existing combustion chamber 4.
  • 3 shows a sectional view of a section of the combustion chamber 4 in the region of the combustion chamber wall 24 with a flow element 49.
  • the heat shield element 26 is spaced apart from the combustion chamber wall 24 and forms an interior space 27 which can be acted upon with a coolant K.
  • a flow element 49 is provided in the interior space 27 targeted setting of a coolant flow inserted.
  • the flow element 49 is essentially cuboid and positively attached to the combustion chamber wall 24.
  • a reduction in the flow cross section for the coolant flow is achieved in the region of the flow element 49, a flow channel 51 for coolant K being formed by the flow element 49, in which the flow velocity v x of the coolant flow increases compared to the flow velocity v 0 upstream of the flow element 49 is.
  • the local increase in the flow velocity in the flow channel 51 causes an increased heat transfer from the hot side 35 of the heat shield element 26 to the coolant K, for example cooling air.
  • a thermally particularly highly stressed wall section 47a of the heat shield element 26 can thus be locally cooled with a higher cooling capacity.
  • the flow element 49 enables a cooling adaptation, the gap dimension in the interior 27 between the cold side 33 and the combustion chamber wall 24 being adapted with regard to the cooling requirement.
  • the heat shield element 26 can have a high-temperature resistant protective layer on the hot side 35 for exposure to very hot combustion gases.
  • a protective layer 31 can be, for example, a ceramic thermal insulation layer.
  • FIG. 4 shows an exemplary embodiment with a modified flow element 49, which is inserted into the interior 27.
  • the flow channel 51 for the coolant K formed by the flow element 49 in the interior 27 varies in the flow direction.
  • the flow cross section in the flow channel 51 initially decreases continuously in the direction of flow and reaches a value which subsequently remains constant for a certain flow path in order to then increase again to a larger flow cross section.
  • This approximately wedge-shaped profile of the flow element 49 leads in the area of the linear rise to a correspondingly proportionally increasing flow velocity v x in the flow channel 51.
  • a combustion chamber lining with a number of heat-resistant as well as stiffened heat shield elements 26 is provided in a preferred embodiment, as described in more detail below with reference to FIGS. 5 and 6 , In this way, a full-surface, largely leak-free combustion chamber lining is formed in the annular space, a so-called combustion chamber liner, which is also particularly efficient by means of the flow element 49 in the interior 27 because it can be cooled locally.
  • FIG. 5 shows a simplified perspective illustration of an exemplary embodiment of a heat shield element 26 and FIG. 6 shows a somewhat enlarged view of the end face of the heat shield element 26 shown in FIG. 5.
  • the heat shield element 26 extends along a longitudinal axis 43 and one perpendicular to the longitudinal axis 43 extending transverse axis 45.
  • the heat shield element 26 comprises a wall 47, the one Has hot side 35 with a hot side surface 55 which can be acted upon by the hot working medium M.
  • a cold side 33 is provided opposite the hot side 35 of the wall 47.
  • the wall 47 has two wall sections 47A, 47B, a first wall section 47A being arranged upstream of a second wall section 47B along the longitudinal axis 43 in the flow direction of the working medium M. Furthermore, the second wall section 47B is inclined relative to the first wall section 47A in the direction of the hot side 35, so that the second wall section 47B forms an inclination angle with the longitudinal axis 43. The inclination is set so that a structural adjustment to the lining of a combustion chamber wall 24 (see FIG. 2) is achieved. Surface regions 57A, 57B are formed on the hot side surface 55 in the first wall section 47A.
  • the surface regions 57A, 57B each have a non-planar, that is to say curved, surface contour along the longitudinal axis 43 and along the transverse axis 45.
  • the surface region 57A is concavely curved in the direction of the transverse axis 45 and convexly curved in the direction of the longitudinal axis 45, so that a saddle surface 59 with a saddle point P s is formed in the surface region 57A.
  • the second surface region 57B has a spherical surface contour and is arranged along the longitudinal axis 43 in the flow direction of the working medium M, for example the hot combustion gas, downstream of the surface region 57A, the surface region 57A merging into the second surface region 57B via a transition region 61.
  • the shape by surface contouring in the surface area 57A, 57B of the first wall section 47A improves the mechanical properties, in particular the rigidity, of the heat shield element 26.
  • the natural vibration modes of the heat shield element 26 are influenced in a targeted manner with respect to the excitation frequency of a combustion vibration.
  • the increase in the rigidity of the heat shield element 26 takes place by means of stiffening of the shape and leads directly to an increase in the mode of operation compared the relevant excitation frequency of a combustion oscillation. Because of this increase in rigidity due to the geometric configuration of the hot side surface in the invention, the heat shield element 26 is clearly superior to the conventional planar heat shield elements.
  • a two-dimensional curved surface contour is embossed on the surface region 57A, 57B both along the longitudinal axis 43 and along the transverse axis 45.
  • a curved surface contour can also be embossed on the cold side 33 or on the surfaces in the second wall section 47B, where this leads to a further improvement in the vibration behavior with regard to a low susceptibility to resonance excitation due to conventional combustion vibration frequencies.
  • a sufficient stiffening of the shape by good two-dimensional surface contouring of the hot side surface 55 in the first wall section already gives good results.
  • a conventional - essentially planar - heat shield element has a typical natural frequency at, for example, 380 Hz, whereas an increase in the natural frequency to 440 Hz could be achieved by the contouring according to the invention with otherwise the same dimensions.
  • already concave and / or convex surface contours with only small radii of curvature increase the rigidity of the heat shield element 26.
  • the configuration according to the exemplary embodiment in FIG. 5 with a combination of a saddle surface contour in the surface region 57A and a spherically concave surface contour in the surface region 57B has proven to be particularly favorable.
  • This shape of the hot side surface 45 viewed linearly in the direction of the longitudinal axis, achieves an S-shaped contour in the first wall section 47A, whereas the second wall section 47B is largely planar.
  • the gas turbine achieves a particularly uniform and low flow loss deflection of the hot working medium M with subsequent inflow into the turbine blading.
  • the S shape also avoids direct flame exposure to the hot side surface 55.
  • this surface contour brings about an improved overflow of the working medium M along the hot side surface 55 from the first wall section 47A to the second wall section 47B.
  • a heat-resistant protective layer 31 is applied to its hot side 35, e.g. a ceramic high temperature resistant thermal barrier coating.
  • a cooling surface 53 is formed on the cold side 33, which is coated with a coolant K, e.g. Cooling air is applied.
  • the coolant flow of the coolant K is set in a targeted manner in that, when installed, the or each heat shield element 26 forms an interior space 27 to which the coolant K can be applied (see FIGS. 2, 3 and 4), in which a flow element 49 is inserted.
  • both the inclusion and the flow guidance of the hot working medium M and the protection of other, possibly less heat-resistant components or components, such as e.g. of the combustion chamber wall 24, is guaranteed against overheating or thermal destruction, targeted cooling of the particularly temperature-stressed areas being achieved when the flow element 49 is used.
  • FIG. 7 shows a perspective exploded view of a section of a combustion chamber wall 24 with a heat shield element 26 and with a flow element 49.
  • the heat shield element 26 is provided as a single-shell hollow body with a cavity 63.
  • the cavity 63 opens in the direction of the combustion chamber wall 24, so that the flow element 49 is enclosed by the single-shell hollow body in the installation situation.
  • the heat shield element 26 has a first wall section 47A and a second wall section 47B inclined with respect to the first wall section 47A.
  • the heat shield element 26 can be fastened on the combustion chamber wall 24 via fastening elements 37, for example by means of a screw connection, a fastening element 37 being assigned a bore 65 in the combustion chamber wall 24.
  • the bore 65 can optionally also be designed as a threaded bore with a thread.
  • the flow element 49 has corresponding cutouts 67.
  • the flow element 49 is approximately wedge-shaped in order to bring about an increase in the flow rate of the coolant K in the region of the thermally more highly stressed first wall section 47A.
  • the flow element 49 is detachably connected to the combustion chamber wall 24, so that an exchange or retrofitting with other flow elements 49 is possible when the cooling elements change.
  • the flow element 49 is attached while maintaining a positive fit between the flow element 49 and the combustion chamber wall 49 in order to ensure mechanical stability on the one hand and precise adjustment of the flow cross section for the coolant K on the other hand.
  • the flow element 49 is provided with bores 65 for attachment to the combustion chamber wall, which bores can be screwed onto the combustion chamber wall 24 from the outside or from the inside.
  • the flow element 49 is a metal part, in particular a metal sheet or a metal molded part.

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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)

Abstract

L'invention concerne une chambre de combustion (4) d'une turbine à gaz, dans laquelle un carburant et de l'air de combustion alimentant cette chambre sont amenés à réagir de manière à générer un fluide moteur (M), la paroi (24) de la chambre de combustion étant munie intérieurement d'un revêtement formé d'une pluralité d'éléments formant bouclier thermique (26), l'élément, ou chaque élément formant bouclier thermique (26) formant, avec la paroi de la chambre de combustion (24) un espace intérieur (27) soumis à l'action d'un réfrigérant (K). L'invention a pour but d'obtenir une chambre de combustion d'une construction relativement simple et offrant un rendement élevé de l'installation. A cet effet, l'invention est caractérisée en ce qu'un élément d'écoulement (49) fournissant un réglage, ciblé localement, du courant réfrigérant, est disposé dans chaque espace intérieur (27).
EP04729621.5A 2003-05-30 2004-04-27 Chambre a combustion Expired - Lifetime EP1636526B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP04729621.5A EP1636526B1 (fr) 2003-05-30 2004-04-27 Chambre a combustion

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP03012441A EP1482246A1 (fr) 2003-05-30 2003-05-30 Chambre de combustion
PCT/EP2004/004442 WO2004106809A1 (fr) 2003-05-30 2004-04-27 Chambre a combustion
EP04729621.5A EP1636526B1 (fr) 2003-05-30 2004-04-27 Chambre a combustion

Publications (2)

Publication Number Publication Date
EP1636526A1 true EP1636526A1 (fr) 2006-03-22
EP1636526B1 EP1636526B1 (fr) 2016-04-13

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Family Applications (2)

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EP03012441A Withdrawn EP1482246A1 (fr) 2003-05-30 2003-05-30 Chambre de combustion
EP04729621.5A Expired - Lifetime EP1636526B1 (fr) 2003-05-30 2004-04-27 Chambre a combustion

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP03012441A Withdrawn EP1482246A1 (fr) 2003-05-30 2003-05-30 Chambre de combustion

Country Status (3)

Country Link
US (1) US8245513B2 (fr)
EP (2) EP1482246A1 (fr)
WO (1) WO2004106809A1 (fr)

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WO2004106809A8 (fr) 2006-02-23
US8245513B2 (en) 2012-08-21
WO2004106809A1 (fr) 2004-12-09
EP1482246A1 (fr) 2004-12-01
US20070062198A1 (en) 2007-03-22
EP1636526B1 (fr) 2016-04-13

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