EP3245451A1 - Chambre de combustion pour turbine à gaz, délimitée par une paroi - Google Patents

Chambre de combustion pour turbine à gaz, délimitée par une paroi

Info

Publication number
EP3245451A1
EP3245451A1 EP16822139.8A EP16822139A EP3245451A1 EP 3245451 A1 EP3245451 A1 EP 3245451A1 EP 16822139 A EP16822139 A EP 16822139A EP 3245451 A1 EP3245451 A1 EP 3245451A1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
chamber wall
gas turbine
bulges
turbine combustor
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
EP16822139.8A
Other languages
German (de)
English (en)
Other versions
EP3245451B1 (fr
Inventor
Carsten Clemen
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
Application filed by Rolls Royce Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG
Publication of EP3245451A1 publication Critical patent/EP3245451A1/fr
Application granted granted Critical
Publication of EP3245451B1 publication Critical patent/EP3245451B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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
    • F23R3/02—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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03041—Effusion cooled combustion chamber walls or domes

Definitions

  • the invention relates to a gas turbine combustion chamber according to the features of the preamble of claim 1.
  • the invention relates to a gas turbine combustor having an inner combustor wall and an outer combustor wall which form an annular combustor.
  • a gas turbine combustor having an inner combustor wall and an outer combustor wall which form an annular combustor.
  • mixing air holes distributed around the circumference are formed, through which admixing air is introduced into the interior of the combustion chamber.
  • the invention relates to a gas turbine combustor as described in WO 2014/149081 A1.
  • a combustion chamber operates according to the "counter swirl doublet mixer concept.”
  • the combustion chamber which can be modularly constructed with individual modules arranged distributed around the circumference, comprises an outer and an inner combustion chamber wall and a head plate, in which recesses
  • the combustion chamber itself has a single-walled construction, so that the outer combustion chamber wall and the inner combustion chamber wall are made, for example, of formed sheet metal in each case two mixed air holes in pairs next to each other, according to the "counter swirl doublet mixer concept". There are thus provided two mixing holes for each fuel nozzle.
  • the mixing air holes are formed in the prior art so that they are provided with a substantially tubular air guide, which extends relatively far into the interior of the combustion chamber.
  • the problem arises that the air ducts of the mixing air holes are relatively long and, as mentioned, protrude into the interior of the combustion chamber and thus into the flame zone. It is only very conditionally possible to cool the air ducts so that they burn off during operation. By such burnup, however, the temperature distribution changes on Combustion chamber exit considerably. This also leads to increased undesirable NOX emissions.
  • the previously provided for the "counter swirl doublet mixer concept" combustion chambers are only limited use.
  • the invention has for its object to provide a gas turbine combustor of the type mentioned above, which avoids the disadvantages of the prior art with a simple structure and simple, cost-effective manufacturability and allows effective supply of admixed air.
  • the object is achieved by the combination of features of claim 1, the dependent claims show further advantageous embodiments of the invention.
  • the respective combustion chamber wall namely both the inner combustion chamber wall and the outer combustion chamber wall in the region of the mixing air holes is bulged to the interior of the combustion chamber wall, wherein the mixing air hole is arranged in the respective bulge.
  • the solution according to the invention thus provides that, distributed around the circumference, analogous to the distribution of the mixed air holes, viewed from the interior of the combustion chamber, convex bulges are formed. These extend in the region of the respective mixing air hole or the pairwise mixing air holes provided in accordance with the "counter swirl doublet mixer concept.” Thus, tubular air ducts do not extend into the interior of the combustion chamber from the mixing air holes, as provided for in the prior art As the one or more mixing holes are provided in the respective bulge, the admixing air passing through the mixing air hole is reliably guided into the inner portion of the interior of the combustion chamber.
  • a plurality of bulges are thus preferably formed distributed on the circumference, which correspond to the number of mixing air holes or mixed air hole pairs.
  • the result is thus a wave-like contouring of the combustion chamber wall distributed around the inner circumference of the annular combustion chamber in the region of the mixing air holes arranged on the circumference.
  • This contouring is provided both on the inner combustion chamber wall and on the outer combustion chamber wall.
  • the bulge preferably starts axially in front of the or the respective mixing air holes and ends axially behind the mixed air holes.
  • axial in this case refers to the direction of flow through the combustion chamber or to its center axis in the sectional view to be considered in each case, since it is an annular combustion chamber, the central axes to be considered for the individual burners arranged on a truncated cone, as well as the prior art shows. The respective center axes are thus only in an axial section plane parallel to the engine axis.
  • the bulges are arranged offset to each other on the inner combustion chamber wall and the outer combustion chamber wall, based on a radial section plane to follow with the provided in the bulges Misch Kunststofflöchern the "counter swirl doublet mixer concept".
  • the invention is not limited to the "counter swirl doublet mixer concept", but it is also possible to provide only a mixed air hole in a bulge.
  • the mixing air holes are arranged in pairs.
  • the bulges preferably have rounded side surfaces in order to improve the flow behavior through the interior of the combustion chamber. It is particularly advantageous if the bulges, based on the flow direction of the combustion chamber, in each case to the combustion chamber wall have an inflow surface, which forms a smaller angle, as an outflow surface. This also serves for efficient flow guidance through the interior of the combustion chamber.
  • the mixed air holes in particular if they are arranged in pairs, have mutually different diameters.
  • the height of the bulges is preferably between 7.5% and 25% of the total height of the interior of the combustion chamber.
  • cooling air holes in particular effusion holes
  • the bulges according to the invention can be produced by deep drawing or pressing the sheet of the combustion chamber by means of suitable tools in the underlying single-walled, made of sheet metal combustion chamber construction. There are thus local bulges from the outside of the respective combustion chamber wall to the interior of the Burner pressed or introduced by a suitable forming process.
  • the mixing air holes can be formed by milling, laser cutting or the like in the bulges.
  • the additional cooling holes / effusion holes can be created by laser drilling or similar methods.
  • FIG. 1 is a schematic representation of a gas turbine engine according to the present invention
  • FIG. 2 is a simplified axial sectional view of a combustion chamber according to the prior art
  • Fig. 3 is a view, analogous to FIG. 2, in a radial section plane according to the prior
  • Fig. 4 is a simplified sectional view of an inventive
  • Fig. 5 is a radial sectional view of the embodiment of FIG. 4 in
  • FIG. 6 is an axial sectional view along section line A of Fig. 5,
  • FIG. 7 is a view, analogous to FIG. 6, according to section line B of FIG. 5, FIG.
  • Fig. 8 is a schematic interior view of a portion of the combustion chamber wall
  • Fig. 9 is a sectional view, analogous to FIG. 4, showing a manufacturing possibility
  • FIG. 10 is a sectional view, analogous to FIG. 5.
  • the gas turbine engine 10 of FIG. 1 is a generally illustrated example of a turbomachine to which the invention may find application.
  • the engine 10 is formed in a conventional manner and comprises in succession an air inlet 1 1, a circulating in a housing fan 12, a medium pressure compressor 13, a high pressure compressor 14, a combustion chamber 15, a high pressure turbine 16, a medium pressure turbine 17 and a low pressure turbine 18 and an exhaust nozzle 19, all of which are arranged about a central engine axis 1.
  • the medium-pressure compressor 13 and the high-pressure compressor 14 each comprise a plurality of stages, each of which has a circumferentially extending fixed fixed Guide vanes 20, which are generally referred to as stator blades and project radially inwardly from the core engine housing 21 in an annular flow channel through the compressors 13, 14.
  • the compressors further include an array of compressor blades 22 projecting radially outwardly from a rotatable drum or disc 26 coupled to hubs 27 of high pressure turbine 16 and mid pressure turbine 17, respectively.
  • the turbine sections 16, 17, 18 have similar stages, comprising an array of fixed vanes 23 projecting radially inward from the housing 21 into the annular flow passage through the turbines 16, 17, 18, and a downstream array of turbine rotor blades 24 projecting outwardly from a rotatable hub 27.
  • the compressor drum or compressor disk 26 and the blades 22 disposed thereon and the turbine rotor hub 27 and the turbine rotor blades 24 disposed thereon rotate about the engine axis 1 during operation.
  • FIG. 2 is a simplified axial sectional view showing an annular combustion chamber having an inner combustion chamber wall 2 and an outer combustion chamber wall 1 and provided with a head plate 29 in which recesses 30 are formed around the circumference (see Fig. 3), which serve to receive fuel nozzles 31, as is known from the prior art.
  • FIGS. 2 and 3 show, in the axial-sectional plane or radial-sectional plane (FIG. 3), a plurality of mixing air holes 4 distributed around the circumference, which serve for supplying mixed air into an interior 5 of the combustion chamber.
  • the mixing air holes 4 are provided with air ducts 32, which project like a tube into the interior 5, as shown in particular in Fig. 2.
  • the reference numeral 33 a combustion chamber head is shown.
  • the reference numeral 34 denotes an outer casing in which the combustion chamber is arranged.
  • Both the inner combustion chamber wall 2 and the outer combustion chamber wall 3 are provided with cooling air holes 25 which serve as Effusionskühllöcher.
  • the respective air ducts 32 are far in the interior 5 of the combustion chamber and are therefore liable to burn.
  • FIG. 4 shows a sectional view analogous to FIG. 2.
  • the through-flow direction 7 is shown with an arrow. It returns the main flow through the fuel nozzle 31.
  • bulges 6 are provided both on the inner combustion chamber wall 2 and on the outer combustion chamber wall 3, which bulges, viewed from the inner space 5, are convex and have rounded contours.
  • the total height H of the combustion chamber is shown in FIG. 4 and depicts the respective height of the inner space 5 between the inner combustion chamber wall 2 and the outer combustion chamber wall 3.
  • the height h of the bulges 6 is also indicated in FIG. 4. It is between 7.5% and 25% of the total height H.
  • FIG. 5 shows a view C according to FIG. 6 and thus a view from the outflow side of the combustion chamber in a radial section plane.
  • the recesses 30 are shown for the fuel nozzles 31.
  • Both the inner combustion chamber wall 2 and the outer combustion chamber wall 3 are distributed around the circumference in the region of the mixing air holes 4 with bulges 6 which extend into the interior 5 of the combustion chamber and thus in the sectional view leads to a wave-shaped contour of the combustion chamber walls 2, 3 ,
  • FIG. 5 shows a simplified representation of tools 35, which are explained in more detail below in conjunction with FIGS. 9 and 10. These tools 35 serve to produce the bulges 6.
  • FIG. 5 shows two sections A and B arranged in the radial direction. Sectional views along these sections A and B are shown in FIGS. 6 and 7.
  • 6 shows a view according to section line A and illustrates the shape and arrangement of the bulges 6. These have an inflow surface 8 and an outflow surface 9 in the throughflow direction 7 (see FIG. It can be seen that the inflow surface 8 is arranged at a shallower angle to the respective combustion chamber wall 2, 3 than the outflow surface 9. This is also illustrated once more in the view of FIG. 8. It can be seen that the bulges 6 need not be circular. The geometry depends on the dimensioning and design of the combustion chamber. Also provided in the respective bulge 6 mixing air holes 4 may be provided with different diameters, analogous to the representation in Fig. 3 and the "counter swirl doublet mixer concept".
  • the walls of the bulge 6 are provided with cooling air holes 25.
  • FIGS. 5 to 7 show that in the region of the mixed air holes, which are located in a central region of the cross section of the annular combustion chamber, alternately the inner combustion chamber wall 2 and the outer combustion chamber wall 3, matching the alternating arrangement of the mixed air holes (see Fig. 3), the bulges 6 according to the invention are provided. These may be dimensioned differently on the inner combustion chamber wall 2 and on the outer combustion chamber wall 3. The height h and thus the penetration depth of the bulges are preferably selected so that the admixing air entering through the mixing air holes 4 is discharged in the same way as in the prior art (see FIG. 3), in which additional tubular air ducts 32 are provided.
  • FIGS. 9 and 10 show, as already indicated in FIG. 5, possibilities for producing the bulges 6 according to the invention.
  • These can be pressed in from outside by suitable tools 35, which act similarly to a deep-drawing tool.
  • suitable tools 35 which act similarly to a deep-drawing tool.
  • the impressing from the outside tools can have a suitably selected shape to the contour of the bulges 6, which results, for example, from FIG. 8.
  • the cooling air holes 25 are then formed, for example by laser drilling or the like, while the mixing air holes 4, for example by laser cutting, can be generated.
  • the radii of the recesses are, for example, 10 to 15 mm in order not to impair the component strength and to allow production by the tools 35. These radii also determine the beginning and the end of the respective bulges both in the axial direction and in the circumferential direction.
  • the bulge 6 is provided with an inflow surface 8 and an outflow surface 9.
  • the mixing air holes 4 may be formed in the inflow surface 8, it is also possible to provide these at the apex of the respective bulge 6.
  • the bulges 6 are, compared to the positions on the inner combustion chamber wall 2 and the outer combustion chamber wall 3, circumferentially offset from each other to supply mixing air according to the "counter swirl doublet mixer concept", as shown in simplified in Fig. 3.
  • the bulges 6 can be formed both symmetrically and asymmetrically, both in the axial direction and in the radial direction. This makes it possible to optimize the flow conditions in the interior 5 of the combustion chamber and to adapt the "counter swirl doublet mixer concept". Overall, this results in a staggered arrangement, as explained for example in FIGS. 5 and 10.

Landscapes

  • 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 pour turbine à gaz, comprenant une paroi interne (2) et une paroi externe (3) qui forment une chambre de combustion annulaire ; des trous (4) destinés à l'air mélangé pratiqués dans la paroi interne (2) et la paroi externe (3) de la chambre de combustion sont répartis sur la circonférence ; la paroi de chambre de combustion (2, 3) respective est bombée vers l'espace interne (5) de la chambre de combustion (15) dans la zone des trous (4) destinés à l'air mélangé, le trou d'air mélangé (4) étant disposé dans la partie bombée (6).
EP16822139.8A 2016-02-01 2016-12-15 Chambre de combustion pour turbine à gaz, délimitée par une paroi Active EP3245451B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102016201452.8A DE102016201452A1 (de) 2016-02-01 2016-02-01 Gasturbinenbrennkammer mit Wandkonturierung
PCT/EP2016/081220 WO2017133819A1 (fr) 2016-02-01 2016-12-15 Chambre de combustion pour turbine à gaz, délimitée par une paroi

Publications (2)

Publication Number Publication Date
EP3245451A1 true EP3245451A1 (fr) 2017-11-22
EP3245451B1 EP3245451B1 (fr) 2019-08-21

Family

ID=57714575

Family Applications (1)

Application Number Title Priority Date Filing Date
EP16822139.8A Active EP3245451B1 (fr) 2016-02-01 2016-12-15 Chambre de combustion pour turbine à gaz, délimitée par une paroi

Country Status (4)

Country Link
US (1) US10670270B2 (fr)
EP (1) EP3245451B1 (fr)
DE (1) DE102016201452A1 (fr)
WO (1) WO2017133819A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3475614B1 (fr) * 2016-06-22 2023-08-02 General Electric Company Ensemble chambre de combustion pour un moteur à turbine

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20200318549A1 (en) * 2019-04-04 2020-10-08 United Technologies Corporation Non-axisymmetric combustor for improved durability
US11940151B2 (en) * 2022-01-12 2024-03-26 General Electric Company Combustor with baffle
CN118548508B (zh) * 2024-07-29 2024-09-27 中国空气动力研究与发展中心空天技术研究所 燃油喷孔出口面积连续可调的主燃级燃油喷嘴及调节方法

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FR1130169A (fr) 1954-09-03 1957-01-31 Rolls Royce Perfectionnements à l'appareillage de combustion des moteurs à turbine à gaz
US3731484A (en) * 1967-11-10 1973-05-08 Lucas Ltd Joseph Apparatus for regulation of airflow to flame tubes for gas turbine engines
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FR2922629B1 (fr) * 2007-10-22 2009-12-25 Snecma Chambre de combustion a dilution optimisee et turbomachine en etant munie
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RU2519014C2 (ru) * 2010-03-02 2014-06-10 Дженерал Электрик Компани Диффузор для камеры сгорания турбины (варианты) и камера сгорания турбины
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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3475614B1 (fr) * 2016-06-22 2023-08-02 General Electric Company Ensemble chambre de combustion pour un moteur à turbine

Also Published As

Publication number Publication date
DE102016201452A1 (de) 2017-08-03
US10670270B2 (en) 2020-06-02
US20180156459A1 (en) 2018-06-07
EP3245451B1 (fr) 2019-08-21
WO2017133819A1 (fr) 2017-08-10

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