EP2644995A1 - Verbesserte Lochanordnung von Auskleidungen einer Brennkammer eines Gasturbinenmotors mit niedriger Verbrennungsdynamik und niedrigen Emissionen - Google Patents

Verbesserte Lochanordnung von Auskleidungen einer Brennkammer eines Gasturbinenmotors mit niedriger Verbrennungsdynamik und niedrigen Emissionen Download PDF

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Publication number
EP2644995A1
EP2644995A1 EP20120161509 EP12161509A EP2644995A1 EP 2644995 A1 EP2644995 A1 EP 2644995A1 EP 20120161509 EP20120161509 EP 20120161509 EP 12161509 A EP12161509 A EP 12161509A EP 2644995 A1 EP2644995 A1 EP 2644995A1
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EP
European Patent Office
Prior art keywords
holes
wall element
hole arrangement
combustion chamber
areal density
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.)
Withdrawn
Application number
EP20120161509
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English (en)
French (fr)
Inventor
Charith Jayatunga
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 EP20120161509 priority Critical patent/EP2644995A1/de
Priority to EP12798272.6A priority patent/EP2831506B1/de
Priority to RU2014142880/06A priority patent/RU2582378C1/ru
Priority to CN201280071988.XA priority patent/CN104204679B/zh
Priority to JP2015502114A priority patent/JP6005836B2/ja
Priority to US14/385,733 priority patent/US20150101335A1/en
Priority to PCT/EP2012/074459 priority patent/WO2013143627A1/en
Publication of EP2644995A1 publication Critical patent/EP2644995A1/de
Withdrawn legal-status Critical Current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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • 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
    • 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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • 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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/44—Combustion chambers comprising a single tubular flame tube within a tubular casing
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00014—Reducing thermo-acoustic vibrations by passive means, e.g. by Helmholtz resonators
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03041—Effusion cooled combustion chamber walls or domes
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03044—Impingement cooled combustion chamber walls or subassemblies
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49229—Prime mover or fluid pump making

Definitions

  • the present invention relates to a housing for a combustion chamber for a gas turbine and to a method for producing a combustion chamber of a gas turbine.
  • the wall elements of the combustion chamber housings are provided with holes through which a gas exchange takes place.
  • GB 2 309 296 A discloses a gas turbine engine combustor wherein the combustor comprises an inner combustor wall and an outer combustor wall. To the combustor wall damping holes are formed. The damping holes are arranged uniformly over the wall section, i.e. the damping holes have the same distances between each other.
  • EP 1 104 871 A1 discloses a combustion chamber for a gas turbine engine, wherein the combustion chamber is a twin wall combustion chamber.
  • An inner wall and an outer wall of the twin wall combustion chamber comprise effusion holes in order to provide an impingement cooling.
  • the effusion holes are uniformly distributed over the effective inner wall or outer wall.
  • EP 1 321 713 A2 discloses an improved flame tube of a combustion chamber of a gas turbine. Cooling air is guidable through apertures of the respective walls of the flame tube.
  • This object may be solved by a housing for a combustion chamber for a gas turbine, by a combustion chamber for a gas turbine and by a method for producing a combustion chamber for a gas turbine according to the independent claims.
  • a housing for a combustion chamber for a gas turbine comprises a wall element which comprises a first hole arrangement and a second hole arrangement.
  • the first hole arrangement comprises first holes through which first holes fluid is streamable.
  • the first hole arrangement further comprises a first areal density of the first holes.
  • the second hole arrangement comprises second holes through which second holes fluid is streamable.
  • the second hole arrangement further comprises a second areal density of the second holes. The first areal density differs from the second areal density.
  • the combustion chamber comprises an inner housing which comprises the features of the above described housing and an outer housing which may also comprise the features of the above described housing.
  • the outer wall element of the outer housing at least partially envelopes the inner wall element of the inner housing such that a gap between the inner wall element and the further outer wall element is formed.
  • the terms “inner” and “outer” relate to a relative position i.e. of the inner and outer wall elements with respect to the distance between the wall element and the flame volume in the combustion chamber.
  • the center axis of the combustion chamber may be a symmetry line of a (e.g. cylindrically formed) combustion chamber (such as a can-type combustion chamber), i.e. passing though the flame region or it may be for example parallel or even coincide with the rotor centre line of the gas turbine (such as an annular combustion chamber).
  • a method for producing a combustion chamber of a gas turbine is presented.
  • a first hole arrangement which comprises first holes is formed into an inner wall element of an inner housing, wherein through the first holes fluid is streamable and wherein the first hole arrangement comprises a first areal density of the first holes.
  • a second hole arrangement which comprises second holes is formed into the inner wall element, wherein through the second holes fluid is streamable and wherein the second hole arrangement comprises a second areal density of the second holes.
  • the first areal density differs from the second areal density.
  • area density surface density
  • a wall element of a housing for a combustion chamber comprises the first hole arrangement with the first areal density and the second hole arrangement with the second areal density.
  • the holes of a wall element are distributed non-uniformly and are particular adapted to respective flow characteristics of a respective fluid which flows along the wall element.
  • the housing for a combustion chamber of a gas turbine may be an inner housing which surrounds for example the combustion volume of the combustion chamber.
  • the housing may further be an outer housing which partially surrounds the inner housing.
  • a twin-walled or double-walled combustion chamber i.e. a double skin liner
  • a gap may exist between the inner housing and the outer housing.
  • a fluid e.g. a cooling fluid/gas, which streams along the outer wall element, may enter through the first and second holes of the outer wall element into the gap for cooling purposes. The fluid may further flow from the gap through the first and second holes of the inner wall element into the combustion space of the combustion chamber for cooling purposes.
  • holes of wall elements of housings for combustion chambers are distributed uniformly.
  • the first hole arrangement and second hole arrangement comprise one and the same areal density of the respective holes.
  • the holes are distributed non-uniformly in the (inner and outer) housing of the combustion chamber.
  • the distribution of the holes may be adapted and customized to the flow parameters of the (burned) fluid of the combustion chamber and to the flow parameters of the cooling gas.
  • the combustion dynamics inside the combustion chamber may be reduced.
  • a longer life of the housing and other combustion components results due to e.g. the reduction of fluctuation in the temperature profile at the wall elements.
  • the turbine efficiency and the operating temperature of the turbine may be increased without affecting the life of the housing of the combustion chamber.
  • the nitrogen (NOx) emissions may be reduced for example by operating the gas turbine with a lean-burn combustion, i.e. by a lower pilot fuel split inside the gas turbine.
  • the distribution of the holes in a non-uniform manner and by arranging the pattern of the holes in a respective hole arrangement the combustion chamber may operate at lower nitrogen (NOx) emissions because for example more air may be fed to the combustion process for providing a lean-burn combustion.
  • the flame temperature is reduced due to the lean-burn combustion.
  • the wall element is formed for at least partially extending along a circumferential direction around the central axis of the combustion chamber.
  • the combustion chamber is formed cylindrically (or conically).
  • the central axis forms e.g. the symmetry axis of the combustion chamber, for example.
  • the first holes of the first hole arrangement are formed into the wall element one after another along the circumferential direction for forming at least one first row of the first holes.
  • the second holes of the second hole arrangement are formed into the wall element one after another along the circumferential direction for forming at least one second row of second holes.
  • the amount of first holes are equal for example to the amount of the second holes seen over the whole circumference, but the areal density for each row of holes varies between the first and second rows of holes.
  • the second holes of the second hole arrangement are formed into the wall element one after another along the circumferential direction for forming at least one second row of second holes. Because the first holes in the first hole arrangement comprise a first areal density which differs from the second areal density of the second holes of the second hole arrangement, the amount of first holes differs for example to the amount of the second holes.
  • the amount of first rows differs from the amount of second rows. Additionally or alternatively, the amount of first holes in the first row differs from an amount of second holes of a second row. This results in a first areal density, which differs from the second areal density, and thus in a non-uniform distribution of first and second holes along the wall element.
  • the first holes of the first hole arrangement are formed into the wall element one after another along a first direction.
  • the first direction differs from the circumferential direction for forming at least one further first row of first holes.
  • the first angle between first direction and the circumferential direction is between approximately 10° and approximately 80°, in particular between approximately 30° and approximately 60°.
  • the first holes are arranged into the wall element such that the further first row runs in a spiral way along the respective (e.g. tubular) wall element.
  • the second holes of the second hole arrangement are formed into the wall element one after another along a second direction.
  • the second direction differs from the circumferential direction and/or from the first direction for forming at least one further second row of the second holes.
  • the second angle between the second direction and the circumferential direction is between approximately 10° and approximately 80°, in particular between approximately 30° and approximately 60°.
  • the respective first and/or second holes are formed one after another along a respective first and second directions such that the respective further first row and the respective further second row may form a helical (i.e. spiral) run around the centre axis along the wall element.
  • an outer wall element of an outer housing is arranged with respect to the inner wall element such that the outer wall element at least partially envelopes the inner wall element and such that a gap between the inner wall element and the outer wall element is formed.
  • a further first hole arrangement is formed into the outer wall element, wherein the further first hole arrangement comprises further first holes through which further first holes a further fluid (e.g. cooling fluid/gas) is streamable.
  • the further first hole arrangement comprises a further first areal density of the further first holes.
  • a further second hole arrangement which comprises further second holes is formed into the outer wall element, wherein through the further second holes a further fluid (e.g. cooling fluid/gas) is streamable, wherein the further second hole arrangement comprises the further second areal density of the second holes.
  • the further first areal density differs from the further second areal density.
  • the total hole area for the inner and or outer wall is distributed over the wall such that bands or areas of different hole density emerges.
  • the criteria for the distribution depend on the flow parameters which may be for example the temperature, the flow velocity, the flow direction and/or the turbulence of the fluid and/or a further fluid.
  • the arrangement of the first holes and the second holes are designed and formed while taking into account the flow parameters of the respective fluid.
  • an effective hole distribution of the holes and hence an improved guidance of the fluid and the further fluid along the respective wall elements is provided.
  • the efficiency of the combustion chamber due to the adapted hole arrangement is achieved.
  • holes of hole arrangements in a wall element may be at the beginning of the method equally distributed and hence comprise an equal areal hole density.
  • some of the holes may be removed from the existing hole arrangements, such that a non-equal distribution and a non-equal hole density between the respective hole arrangements are formed.
  • it is measured how the total hole area is reduced in a flow test as confirmation.
  • it is calculated how to machine and arrange the respective holes to get the nominal flow parameters and to achieve a good damping characteristic.
  • the respective holes are distributed in the respective hole arrangements, so that an uneven distribution and/or an uneven areal density of holes is formed, in order to match up with calculated nominal flow parameters and the total effective flow area for the combustion chamber, respectively.
  • combustion dynamics of the fluid inside the combustion chamber may be reduced.
  • the inner wall elements and the outer wall elements are perforated with holes in a non-uniform and customized manner.
  • the lifetime for the combustion chamber component and the downstream located turbine stage components as a result of reduced flame fluctuations and temperature profiles is achieved.
  • the NOx emissions are reduced, because due to the reduced combustion dynamics a lower pilot fuel split (pilot fuel/[pilot fuel + main fuel]) may be applied.
  • Fig. 1 shows a housing for a combustion chamber 100 for a gas turbine.
  • the housing comprises a wall element 101 which comprises a first hole arrangement I and a second hole arrangement II.
  • the first hole arrangement I comprises first holes 110 through which first holes 110 fluid is streamable.
  • the first hole arrangement I comprises a first areal density of the first holes 110.
  • the second hole arrangement II comprises second holes 120 through which second holes 120 fluid is streamable.
  • the second hole arrangement II comprises a second areal density of the second holes 120.
  • the first areal density differs from the second areal density. That is that the amount of first holes 110 per area unit differs from the amount of second holes 120 per area unit. In other words, the first holes 110 are distributed with a different pattern and/or with a different amount and/or with a different size (e.g. hole diameter) with respect to the second holes 120 in the second hole arrangement II.
  • the first hole arrangement I, the second hole arrangement II and for example a third hole arrangement III comprise the same areal size. Furthermore, the first hole arrangement I, the second hole arrangement II and the third hole arrangement III may define the areal unit which may define the respective first, second and/or third areal density of the holes.
  • the density of the first holes 110 within the first hole arrangement I is higher than the second areal density and third areal density of the respective second hole arrangement II and third hole arrangement III, respectively.
  • More holes may be arranged at the upstream front end of the wall element 101 because this is where the flame is located.
  • the first hole arrangement I may have three first rows 111
  • the more downstream located second hole arrangement II may have two second rows 121
  • the farther downstream located third hole arrangement III may have one third row 131.
  • the combustion chamber 100 comprises a burner section 104 (e.g. a front end section) at an upstream location of the combustion chamber 100 with respect to a flow direction of the fluid along the central axis 102 of the combustion chamber 100.
  • a burner section 104 e.g. a front end section
  • the combustion gas exits the combustion chamber 100 and flows further to the turbine stages of the gas turbine, for example.
  • the areal density of the respective holes 110, 120, 130 decreases from the upstream end to the downstream end of the combustion chamber 100.
  • the first holes 110 of the first hole arrangement I are formed into the wall element 101 one after another along a circumferential direction 103 for forming first rows 111 of the first holes 110.
  • the second holes 120 of the second hole arrangement II are formed into the wall element 101 one after another along the circumferential direction 103 for forming e.g. two second rows 121 of second holes 120.
  • the third holes 113 of the third hole arrangement III are formed into the wall element 101 one after another along the circumferential direction 103 for forming at least three third rows 131 of the third holes 130.
  • the amount of holes 110, 120, 130 and the amount of rows 111, 121, 131 decrease along the direction from the upstream end of the combustion chamber 100 to the downstream end of the combustion chamber 100.
  • the distance between the two second rows 121 is smaller than the distance between the third rows 131, for example.
  • the distance between the first rows 121 at an upstream end of the combustion chamber 100 may be half of the distance between the third rows 131 at the downstream section of the combustion chamber 100.
  • the hole arrangement I, II, III as shown in Fig. 1 may be applied to an inner wall element 501 (see Fig. 5 ) (inner liner). Due to the non-uniform hole distribution along the central axis 102 from an upstream end of the combustion chamber 100 to a downstream end of the combustion chamber 100 the areal density at the downstream part is lower than the areal density of the holes at an upstream part of the combustion chamber. Furthermore, also a proper effusion cooling in particular at the upstream part of the wall element 101 compared to a uniform arranged hole arrangement is achieved. Furthermore, by the hole distribution as shown in Fig. 1 proper damping characteristics of the combustion dynamics within the combustion chamber 100 is achieved. The arrangement of the axial rows 111, 121, 131 results on the basis of a desired reduction of the combustion chamber effective area and a desired mass flow of the cooling fluid through the respective holes 110, 120, 130 through the inner wall, respectively.
  • Fig. 2 shows the combustion chamber 100, wherein the wall element 101 comprises the first hole arrangement I and the second hole arrangement II.
  • the first holes 110 of the first hole arrangement I are formed into the wall element 101 one after another along a first direction 201.
  • the first direction 201 differs from the circumferential direction 103 for forming at least one further first row 211 of first holes 110.
  • the second holes 120 of the second hole arrangement II are formed into the wall element 101 one after another along a second direction 202.
  • the second direction 202 differs from the circumferential direction 103 for forming at least one further second row 221 of second holes 120.
  • the further first rows 211 may comprise for example two first holes 110.
  • the further second row 221 comprises for example three second holes 120.
  • the areal density of the second holes 120 in the second hole arrangement II is higher than the areal density of the first holes 110 in the first hole arrangement I.
  • a helical (spiral) run around the center axis 102 along the wall element 101 is formed.
  • the respective holes 110, 120 in Fig. 2 are arranged in a diagonal manner (in a spiral pattern) with respect to the circumferential direction 103.
  • the housing comprising the hole pattern as shown in Fig. 2 may be applied for an outer housing with an outer wall element 502 (see Fig. 5 ).
  • the first direction and the second direction of the diagonal further first rows 211, 221 may be in the same direction as a spiral and helical motion of the combustion gases inside the combustion chamber 100.
  • the spacing between two adjacent diagonal further rows 211, 221 may either be uniform or non-uniform along the circumferential direction 103, depending on the required flow parameters through the respective holes 110, 120, 130.
  • a combustion chamber 100 which comprises the inner housing shown in Fig. 1 and the outer housing shown in Fig. 2 has the surprising effects of efficient cooling properties, efficient damping of flame dynamics and stable flame characteristics in the combustion chamber.
  • Fig. 3 shows a more abstract view of the hole pattern as shown in Fig. 2 .
  • a hole pattern of an outer wall 502 (see Fig. 5 ) of an outer housing of the combustion chamber 100 is shown.
  • the first hole arrangement I and the second hole arrangement II are shown.
  • the first holes 110 are arranged one after another long further first rows 211.
  • the further first rows 211 extend along the first direction 201. Between the first direction 201 und the circumferential direction 103, the first angle ⁇ 1 is defined.
  • the second holes 120 are arranged in the second hole arrangement II one after another along the second direction 202 and form the further second rows 221. Between the second direction 202 and the circumferential direction 103 the second angle ⁇ 2 is defined.
  • the further first rows 211 and the further second rows 221 have a spiral (diagonal) run with respect to the circumferential direction 103.
  • the distance between the respective further rows 211, 221 are different between each other.
  • the first hole arrangement I comprises three pairs of further first rows 211, wherein between each pair of further first rows 211 a larger distance exists than between each of the two further first rows 211 which defines a respective pair of further first rows 211.
  • the second hole arrangement II comprises two pairs of further second rows 221 and one further second row arrangement comprising three further second rows 221.
  • each further row 211, 221 vary such that a non-uniform distribution of holes 110, 120 is provided.
  • Fig. 4 shows an abstract view of a hole pattern as shown in schematically in Fig. 1 .
  • a hole pattern shown in Fig. 4 may be beneficial when being applied to an inner wall 501 (see Fig. 5 ) of an inner housing of the combustion chamber 100.
  • First rows 111 of first holes 110 and second rows 121 of second holes 120 are arranged one after another along the axial direction 102, wherein the first rows 111 and the second rows 121 are parallel with respect to the circumferential direction 103.
  • the distance between the first rows 111 in the first hole arrangement I are smaller than the distances between the second rows 121 of the second hole arrangement II.
  • FIG. 5 shows for a better overview a cross-section of a double wall can type of combustion chamber 100.
  • An inner wall 501 of an inner housing envelopes a burner volume of the combustion chamber 100.
  • an outer wall 502 of an outer housing surrounds the inner wall 501 in such a way that a gap is provided.
  • a cooling fluid stream 503 is streamable through the respective holes 110, 120 of the outer wall 502 into the gap.
  • the cooling fluid stream 503 form at least a part of the cooling fluid stream 504 streaming from the gap between the two wall elements 501, 502 through the holes of 110, 120, 130 of the inner wall 501 into the combustion chamber 100.
  • the cooling fluid stream 504 may be smaller or greater than the cooling fluid stream 503 depending on if cooling fluids has been added or removed in the gap between the two wall elements 501 and 502.
  • the inner wall 501 and the outer wall 502 surround the center axis 102 and thereby form a tubular shaped section of the combustion chamber 100.
  • Fig. 6 shows a method of calibrating and arranging a desired hole arrangement I, II, III of an inner wall element 501 and an outer wall element 502.
  • the initial combustion chamber design is defined.
  • the initial combustion chamber design may comprise an uniform or non-uniform distributed hole pattern in the inner wall element 501 and/or in the outer wall element 502.
  • the combustion chamber is operated, measured or analysed under nominal operating conditions such that the inner wall element 501 and the outer wall element 502 are exposed to the cooling fluid stream 503 and to the further cooling fluid stream 504, respectively.
  • the cooling fluid flows with its respective operating flow parameter through the respective holes of the inner wall element 501 and outer wall elements 502.
  • step 602 the hole arrangements I, II, III of the inner wall element 501 is decided.
  • the effective area of the inner wall element 501 is determined by the total number of holes 110, 120, 130 of the inner wall element 501.
  • step 603 the hole arrangements I, II, III of the outer wall element 502 is decided.
  • the effective area of the outer wall element (outer liner) 502 is determined by the total number of holes 120, 130, 140 on the wall of the outer wall element 502.
  • step 605 the total combustion chamber 100 effective area is determined on a basis of the hole arrangements I, II, III of the inner wall element 501 and the hole arrangements I, II, III of the outer wall element 502.
  • the flow parameters of the fluid e.g. the velocity of the further cooling fluid stream 504 exiting the inner wall element 501 into the combustion space of the combustion chamber 100 is determined (see step 604).
  • step 606 the determined value of the flow parameters of the cooling fluid 503, 504 and the geometric parameter of the combined inner and outer wall elements 501, 502 (i.e. the combustion chamber 100) are compared to nominal values of e.g. velocity of the cooling fluid 503, 504 and the effective area of the combustion chamber 100.
  • step 607 the first areal density, the further first areal density, the second areal density and/or the further second areal density of the respective holes in the inner wall element 501 and/or the outer wall element 502 and thus the respective hole pattern is individually amended until the nominal values of the flow/geometric parameters are reached.
  • the final design of the hole pattern of the inner wall element 501 and the outer wall element 502 is achieved (see step 608).
  • a customized and optimized wall pattern of the inner wall element 501 and the outer wall element 502 is achieved under real operating conditions of the combustion chamber, so that an optimized fluid flow and an effective combustion chamber 100 is designed.
  • the hole pattern is calculated and distributed equally over a given surface.
  • the hole pattern within the given surface are determined balancing the requirements on damping with that of distributing cooling air over a surface using an iterative process as shown in Fig. 6 and as described above.
  • the hole patterns are customized to the operating conditions of the combustion chamber 100 and the gas turbine to which the combustion chamber 100 is mounted.

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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)
EP20120161509 2012-03-27 2012-03-27 Verbesserte Lochanordnung von Auskleidungen einer Brennkammer eines Gasturbinenmotors mit niedriger Verbrennungsdynamik und niedrigen Emissionen Withdrawn EP2644995A1 (de)

Priority Applications (7)

Application Number Priority Date Filing Date Title
EP20120161509 EP2644995A1 (de) 2012-03-27 2012-03-27 Verbesserte Lochanordnung von Auskleidungen einer Brennkammer eines Gasturbinenmotors mit niedriger Verbrennungsdynamik und niedrigen Emissionen
EP12798272.6A EP2831506B1 (de) 2012-03-27 2012-12-05 Verbesserte lochanordnung von auskleidungen einer brennkammer eines gasturbinenmotors mit niedriger verbrennungsdynamik und niedrigen emissionen
RU2014142880/06A RU2582378C1 (ru) 2012-03-27 2012-12-05 Усовершенствованная группа отверстий футеровок камеры сгорания газотурбинного двигателя с низкими динамикой горения и выделениями
CN201280071988.XA CN104204679B (zh) 2012-03-27 2012-12-05 低燃烧动态和排放的燃气涡轮发动机的燃烧室衬套的改进孔排列
JP2015502114A JP6005836B2 (ja) 2012-03-27 2012-12-05 燃焼力学及び排出が小さいガスタービンエンジンの燃焼チャンバ―のライナにおける改良型孔部配置
US14/385,733 US20150101335A1 (en) 2012-03-27 2012-12-05 Hole arrangement of liners of a combustion chamber of a gas turbine engine with low combustion dynamics and emissions
PCT/EP2012/074459 WO2013143627A1 (en) 2012-03-27 2012-12-05 An improved hole arrangement of liners of a combustion chamber of a gas turbine engine with low combustion dynamics and emissions

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EP12798272.6A Not-in-force EP2831506B1 (de) 2012-03-27 2012-12-05 Verbesserte lochanordnung von auskleidungen einer brennkammer eines gasturbinenmotors mit niedriger verbrennungsdynamik und niedrigen emissionen

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Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102016207057A1 (de) * 2016-04-26 2017-10-26 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinenbrennkammer
RU173450U1 (ru) * 2016-11-15 2017-08-28 федеральное государственное бюджетное образовательное учреждение высшего образования "Ульяновский государственный технический университет" Жаровая труба камеры сгорания газотурбинного двигателя с демпфирующими полостями
US20180266687A1 (en) * 2017-03-16 2018-09-20 General Electric Company Reducing film scrubbing in a combustor
DE102019105442A1 (de) 2019-03-04 2020-09-10 Rolls-Royce Deutschland Ltd & Co Kg Verfahren zur Herstellung eines Triebwerksbauteils mit einer Kühlkanalanordnung und Triebwerksbauteil

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2309296A (en) 1995-10-11 1997-07-23 Europ Gas Turbines Ltd Gas turbine engine combuster
EP1104871A1 (de) 1999-12-01 2001-06-06 Alstom Power UK Ltd. Brennkammer für eine Gasturbine
EP1321713A2 (de) 2001-12-21 2003-06-25 Nuovo Pignone Holding S.P.A. Flammrohr oder Bekleidung für die Brennkammer einer Gasturbine mit niedriger Schadstoffemission
US20060196188A1 (en) * 2005-03-01 2006-09-07 United Technologies Corporation Combustor cooling hole pattern
US20070271926A1 (en) * 2006-05-26 2007-11-29 Pratt & Whitney Canada Corp. Noise reducing combustor
US20090013530A1 (en) * 2007-07-09 2009-01-15 Nagaraja Rudrapatna Method of producing effusion holes
US20100077763A1 (en) * 2008-09-26 2010-04-01 Hisham Alkabie Combustor with improved cooling holes arrangement

Family Cites Families (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4296606A (en) * 1979-10-17 1981-10-27 General Motors Corporation Porous laminated material
JPH0660740B2 (ja) * 1985-04-05 1994-08-10 工業技術院長 ガスタービンの燃焼器
SU1373045A1 (ru) * 1986-05-26 1996-12-20 В.М. Кофман Охлаждаемый корпус
CN1012444B (zh) * 1986-08-07 1991-04-24 通用电气公司 冲击冷却过渡进气道
GB9127505D0 (en) * 1991-03-11 2013-12-25 Gen Electric Multi-hole film cooled afterburner combustor liner
US5241827A (en) * 1991-05-03 1993-09-07 General Electric Company Multi-hole film cooled combuster linear with differential cooling
US5687572A (en) * 1992-11-02 1997-11-18 Alliedsignal Inc. Thin wall combustor with backside impingement cooling
JP3619626B2 (ja) * 1996-11-29 2005-02-09 株式会社東芝 ガスタービン燃焼器の運転方法
RU2162194C1 (ru) * 1999-11-24 2001-01-20 Общество с ограниченной ответственностью Научно-производственное предприятие "ЭСТ" Камера сгорания
US6513331B1 (en) * 2001-08-21 2003-02-04 General Electric Company Preferential multihole combustor liner
US6964170B2 (en) * 2003-04-28 2005-11-15 Pratt & Whitney Canada Corp. Noise reducing combustor
US7036316B2 (en) * 2003-10-17 2006-05-02 General Electric Company Methods and apparatus for cooling turbine engine combustor exit temperatures
EP1832812A3 (de) * 2006-03-10 2012-01-04 Rolls-Royce Deutschland Ltd & Co KG Gasturbinenbrennkammerwand mit Dämpfung von Brennkammerschwingungen
FR2941287B1 (fr) * 2009-01-19 2011-03-25 Snecma Paroi de chambre de combustion de turbomachine a une seule rangee annulaire d'orifices d'entree d'air primaire et de dilution
US9897320B2 (en) * 2009-07-30 2018-02-20 Honeywell International Inc. Effusion cooled dual wall gas turbine combustors
US8739546B2 (en) * 2009-08-31 2014-06-03 United Technologies Corporation Gas turbine combustor with quench wake control
US8225591B2 (en) * 2010-08-02 2012-07-24 General Electric Company Apparatus and filtering systems relating to combustors in combustion turbine engines

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2309296A (en) 1995-10-11 1997-07-23 Europ Gas Turbines Ltd Gas turbine engine combuster
EP1104871A1 (de) 1999-12-01 2001-06-06 Alstom Power UK Ltd. Brennkammer für eine Gasturbine
EP1321713A2 (de) 2001-12-21 2003-06-25 Nuovo Pignone Holding S.P.A. Flammrohr oder Bekleidung für die Brennkammer einer Gasturbine mit niedriger Schadstoffemission
US20060196188A1 (en) * 2005-03-01 2006-09-07 United Technologies Corporation Combustor cooling hole pattern
US20070271926A1 (en) * 2006-05-26 2007-11-29 Pratt & Whitney Canada Corp. Noise reducing combustor
US20090013530A1 (en) * 2007-07-09 2009-01-15 Nagaraja Rudrapatna Method of producing effusion holes
US20100077763A1 (en) * 2008-09-26 2010-04-01 Hisham Alkabie Combustor with improved cooling holes arrangement

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EP2831506A1 (de) 2015-02-04
EP2831506B1 (de) 2016-04-06
WO2013143627A1 (en) 2013-10-03
RU2582378C1 (ru) 2016-04-27
US20150101335A1 (en) 2015-04-16
JP2015511696A (ja) 2015-04-20
CN104204679A (zh) 2014-12-10
CN104204679B (zh) 2016-04-20
JP6005836B2 (ja) 2016-10-12

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