EP3132202A1 - Umführungs-hitzeschildelement - Google Patents
Umführungs-hitzeschildelementInfo
- Publication number
- EP3132202A1 EP3132202A1 EP16713409.7A EP16713409A EP3132202A1 EP 3132202 A1 EP3132202 A1 EP 3132202A1 EP 16713409 A EP16713409 A EP 16713409A EP 3132202 A1 EP3132202 A1 EP 3132202A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- heat shield
- wall
- combustion chamber
- shield element
- edge
- 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
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
-
- 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
- F23R3/007—Continuous combustion chambers using liquid or gaseous fuel constructed mainly of ceramic components
-
- 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
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/50—Combustion chambers comprising an annular flame tube within an annular 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
- 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
- F23R3/60—Support structures; Attaching or mounting means
-
- 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
- F23R2900/03042—Film 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
- F23R2900/03043—Convection cooled combustion chamber walls with means for guiding the cooling air flow
Definitions
- the invention relates to a heat shield element, in particular for lining a combustion chamber.
- the invention further relates to an annular combustion chamber and a gas turbine plant.
- the operator of the gas turbine can be forced to switch off his gas turbine if it is not possible for him to further reduce the output of his gas turbine without simultaneously exceeding the carbon monoxide emission limit.
- bypass air into the combustion chamber ie from compressor discharge air, which is diverted in front of the burner and guided into the combustion chamber behind the combustion zone, remedies this problem.
- the walls of high tempera ⁇ turgasreaktoren for example, operated by pressure gas turbine combustors, a suitable shielding of their support structure against attack of the hot gas. Ceramic materials are particularly suited to build a support structure shielding the heat shield due to its high temperature resistance ⁇ ness, corrosion resistance and its low thermal conductivity ⁇ compared to metallic materials.
- Such a heat shield is ⁇ example, in EP 0558540 Bl and described may have to be modified accordingly in the ⁇ mentation as a bypass (bypass) of the compressor discharge air.
- the heat shield element has a wall with a combustion chamber inner side facing the hot side and a cold side respectivelylie ⁇ restrictive.
- a circumferential edge extends beyond the cold side on the back. It is provided that in the peripheral edge a plurality of bores are introduced, can flow through the cooling air into the combustion chamber. Furthermore, it is provided that at a distance from the wall, a second partial wall is present, which extends between two opposite edge portions. A downstream gelege- ner edge portion of the circumferential edge extends ever ⁇ but only to the part of the wall and not beyond.
- a partition wall is arranged, which extends from the partial wall to the rear height of the two adjoining edge portions. In this way, it will continue to he ⁇ enables to guide a bypass air flow to the wall part, which then can leak between the opposing edge portions downstream.
- a disadvantage of the previous solution is that for the advantageous inflow of the bypass air, an offset in the heat shield elements is necessary or a higher pressure loss must be accepted by a deflection in a subsequent gap in purchasing.
- An object of the invention is therefore to provide a Hitzeschildele ⁇ ment, which allows the supply of bypass air, at the same time high life and the possible easy and inexpensive to manufacture and assemble.
- Another object of the invention is to specify a ring combustion chamber ⁇ with a corresponding heat shield.
- the generic heat shield element is used in particular for use as a lining of a combustion chamber.
- the heat shield element initially comprises a wall which has a hot side which can be acted upon by a hot medium and a cold side which is opposite to the hot side.
- the heat shield element comprises an edge adjacent to the wall and surrounding the wall. In this case, the edge extends from the hot side pointing away raised above the cold side.
- the edge can be divided into two opposing first edge portions.
- At one end of the wall is a second edge portion, which connects the two first edge portions with each other and extends substantially transverse to the first edge portions.
- a third Randab ⁇ section Opposite to the second edge portion is a third Randab ⁇ section , which also connects the two first edge portions with ⁇ each other and extends substantially transverse to the first edge portions.
- the wall has at least one opening gap, whereby the wall in a first wall portion on one side of the opening gap and a second wall portion the other side of the opening gap is divided.
- Wei ⁇ terhin is provided that adjoins the second wall portion adjacent to the opening gap from the hot side wegwei ⁇ send partition.
- the second wall section on the cold side is surrounded by sections of the two first edge sections, the second edge section and the partition wall arranged opposite the second edge section.
- the first wall portion is also surrounded by sections voltage splitting the first two edge portions, the third edge portion and the opposite to the third edge portion disposed adjacent to the partition wall ⁇ Publ.
- the In ⁇ nere of the heat shield element is divided into two.
- the first chamber acts as an extension of the bypass channel.
- the heat shield element integrates homogeneously into the bypass. Characterized in that the gap opening is directly adjacent to the partition wall in particular in ⁇ sondere a small distance between a bypass channel and the ⁇ ffungsspalt a homogeneous flow profile with a low pressure drop across the opening gap is favored.
- the opening gap along the entire partition between the two opposing first Randabschnit- th extends, so that a uniform bypass flow with suffi ⁇ chendem mass flow can be achieved.
- the shape or the course of the peripheral edge and the partition on the cold side is initially irrelevant. To that extent, the edge portions and the partition wall can to each other and / or within the portions of bends or cracks and thus have a different height on the cold side on ⁇ . However, it is advantageous if the circulating Edge and the partition extends to a ent removed from the cold side ⁇ located free end.
- the free end ent ⁇ a speaks in this case from the hot side or from the Kaltsei ⁇ te spaced surface (without kinks or jumps).
- the free end is planar.
- the planar shape of the Hitzeschildele ⁇ ment on the back facing away from the hot side be ⁇ favorable both the assembly and the production.
- the partition wall is inclined towards the opening gap.
- the partition wall is located over the opening gap in sections.
- the partition wall has a plurality of holes ⁇ whose axes are directed to the surface of the cold side of the ers ⁇ th wall portion. If the second chamber is designed comparatively flat, there can be a conventional, large-scale impact cooling.
- the ge ⁇ for used cooling air causes in addition to the blocking of the open gap in the absence of bypass current. For this purpose, the cooling air can flow from the second chamber through the holes in the partition into the first chamber.
- a fastening device is arranged, which advantageously extends perpendicularly pointing away from the wall of the hot side.
- the heat shield element is made of metal.
- a hit ⁇ zeschildelement is realized as a cast component.
- a generic annular combustion chamber comprising a reliedura ⁇ le and a number of heat shield elements, which are releasably secured to the combustion chamber interior facing inside of the outer shell.
- the annular combustion chamber comprises a so-called Bypassplenum, extending over the circumference of the outer shell annular channel through which an air bypass flow is passed in the bypass mode.
- the annular combustion channel can be supplied through openings of the bypass air stream, the annular channel having a side facing the combustion chamber inside the annular gap through which the bypass air flow can be guided to the combustion chamber interior.
- the annular channel and the annular gap can be performed circumferentially. So ⁇ far a reasonably uniform distribution of the bypass air flow is ensured over the circumference, the annular channel and / or the annular gap can also be interrupted several times and thus consist of individual segment sections.
- a novel annular combustion chamber is created by the use of a plurality of the previously described inventive and / or advantageous heat shield elements.
- the heat shield ⁇ elements are arranged such that the first chambers come to rest on the annular gap. In this respect are on one side of the annular gap, the partition and on the other side of the annular gap of the third edge portion. This allows a particularly advantageous flow of the bypass air flow out of the annular gap through the first chamber and through the opening gap in the individual heat shield elements.
- the outer shell has openings for the impact cooling of the heat shield elements.
- openings for the impingement cooling of the first wall section are arranged in the first chamber in the annular channel of the outer shell and in these openings tubular Chen are arranged, which extend to the hot side over the outer shell also extend into the first chambers.
- ⁇ cooling air can be selectively directed to the first wall portion of the first chamber.
- the heat shield element rests at least in sections with the free end on the outer shell. Due to the support, a transverse flow between the free end and the outer shell is largely prevented. Obviously, it is particularly advantageous if the support is provided on the peripheral edge and along the partition wall on the outer shell.
- a sealing means between the free end of the heat shield element and the outer shell is seen ⁇ before.
- the sealant is not present in sections, but circumferentially.
- the sealing means is made of an elastic material, so that despite slight deviation in the shape of the free end and / or the outer shell and in vibrations a reliable tightness is achieved.
- first variant and the second variant is combined for sealing by sections an immediate support of the free end is provided on the outer shell and sections, in ⁇ particular in areas with higher pressure difference, a sealant between the free end and the outer shell before ⁇ handen.
- the object directed to a gas turbine plant is achieved by a gas turbine plant having an annular combustion chamber according to the invention.
- FIG. 1 shows the cold side of a heat shield element according to FIG.
- FIG. 2 shows the cold side of a heat shield element according to FIG.
- FIG. 4 shows the hot side of a heat shield element according to the invention
- FIG. 5 shows the bypass concept
- FIG. 6 shows the cooling air management
- FIG. 7 shows a detail of the annular combustion chamber with heat shield elements according to the invention.
- FIG. 8 shows a representation of a gas turbine according to the invention in a longitudinal section according to an embodiment.
- FIGS 1 to 4 show schematically and by way of example a metallic heat shield element 1 according to the invention, with egg ⁇ ner wall 3, which one with a hot medium
- FIGS. 1 to 3 show the cold side 5 and FIG. 4 shows the hot side 4.
- Adjacent to the wall 3 is an encircling edge 6 which extends beyond the plane of the cold side 5 and has a free end 7 remote from the cold side 5.
- the two first opposing edge sections 56 and a second edge section 57 extending transversely to the first edge sections 56 and a third edge section 58 opposite thereto are gripped
- Partition 8 extends from the cold side 5 of the wall 3 to the height of the free end 7 between two opposite, formed by the edge 6 sides 9, so that on the cold side 5 of the wall 3 two separate first and two ⁇ te chambers 10, 11 are formed and the first chamber 10 egg NEN opening gap 12 is provided from the cold side to the hot side 5 4 on ⁇ which connects directly to the partition 8 and extending along the entire partition wall. 8
- the wall 3 is subdivided into two sections, namely once into a first wall section 51 and a second wall section 52.
- the partition 8 is inclined to the opening gap 12 and has a plurality of bores 13, whose axes 14 are directed to the surface of the cold side 5 in the first chamber 10.
- a fastening device 15 is arranged, which extends substantially perpendicularly from the wall 3 away.
- An assembly of the heat shield element 1 takes place in ⁇ example via a connected to the fastening device 15 plate spring package.
- FIGs 5 and 6 show a section through an annular combustion chamber 2 with a number of heat shield elements 1 according to the invention.
- the annular combustion chamber 2 of Figure 5 comprises an outer shell 16, a number of heat shield elements 1 according to the invention, which are releasably secured to the inside of the outer shell 16, and a bypass plenum, extending over the circumference of the outer shell 16 annular channel 17 through which in bypass operation, an air bypass flow is passed, with an annular gap 18 to the combustion chamber ⁇ inner 19 out.
- the heat shield elements 1 are now arranged on ⁇ order that their first chambers 10 at the annular gap 18 to lie come.
- metallic heat shield elements 1 In addition to the metallic heat shield elements 1 according to the invention comprises the combustion chamber 2 upstream of the metallic heat shield elements 1 more rows of Kerami ⁇ 's heat shield elements 24, of which in the figure 5, only one is indicated, as well as downstream of the metallic heat shield elements 1 according to the invention, a series of further metallic heat shield elements 25, but without opening gaps 12.
- Figure 6 explains the cooling air management.
- Bypass air 26 passes from the annular channel 17 into the first chamber 10 of the Hitzeschildele ⁇ elements 1 and passes through opening gaps 12 in the combustion ⁇ chamber interior 19.
- the outer shell 16 has first openings 20 for the impingement cooling 27 of the heat shield elements 1, in particular for their second chambers 11. Through the bores 13 in the partition wall 8, the air used for baffle 27 of the second chamber 11 can continue to be used to block the opening gap 12 against hot gas from the Brennschinne ⁇ ren 19 (see sealing air 28).
- tubes 22 are arranged, which extend into the first chambers 10. This arrangement serves for the impingement cooling 29 of the first chambers 10.
- FIG. 7 shows a section of the annular combustion chamber 2 with heat shield elements 1 according to the invention, ceramic heat shield elements 24 and further metallic heat shield elements 25 in plan view.
- FIG. 8 shows schematically and exemplarily a ⁇ OF INVENTION dung modern gas turbine system 23 in a longitudinal section.
- This includes a compressor section 30, a Brennschab- section 31 and a turbine section 32.
- a shaft 33 he ⁇ extends through all sections of the gas turbine system 23.
- In the compression section 30 is the shaft 33 with rings of compressor blades 34 and turbine section 32 with Wreaths of turbine blades 35 equipped.
- Wheels of compressor guide vanes 36 are located between the rotor blade rings in the compressor section 30 and rings of turbine guide vanes 37 in the turbine section 32.
- the guide vanes extend from the housing 38 of the gas turbine installation 23 substantially in the radial direction to the shaft 33.
- air 39 is drawn in through an air inlet 40 of the compressor section 30 and compressed by the compressor blades 34.
- the compressed air is supplied to a burner chamber section 31 arranged in the ⁇ combustion chamber 2, which is configured in the present embodiment as an annular combustion chamber 2.
- a gaseous or liquid fuel is injected via at least one burner 42.
- the resulting air-fuel mixture is ignited and burned in the combustion chamber 2.
- the hot flow path 43 the hot flow
- the Turbinenleitschaufein 37 serve as nozzles for optimizing the momentum transfer to the blades 35.
- the induced by the im ⁇ pulse transfer rotation of the shaft 33 is used to drive a consumer, such as an electric generator.
- the expanded and cooled combustion gases are finally discharged through an outlet 44 from the gas turbine plant 23.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Ceramic Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102015205975.8A DE102015205975A1 (de) | 2015-04-02 | 2015-04-02 | Umführungs-Hitzeschildelement |
PCT/EP2016/056881 WO2016156370A1 (de) | 2015-04-02 | 2016-03-30 | Umführungs-hitzeschildelement |
Publications (2)
Publication Number | Publication Date |
---|---|
EP3132202A1 true EP3132202A1 (de) | 2017-02-22 |
EP3132202B1 EP3132202B1 (de) | 2018-09-19 |
Family
ID=55646578
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP16713409.7A Not-in-force EP3132202B1 (de) | 2015-04-02 | 2016-03-30 | Umführungs-hitzeschildelement |
Country Status (4)
Country | Link |
---|---|
EP (1) | EP3132202B1 (de) |
CN (1) | CN107076418A (de) |
DE (1) | DE102015205975A1 (de) |
WO (1) | WO2016156370A1 (de) |
Families Citing this family (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102012204103A1 (de) * | 2012-03-15 | 2013-09-19 | Siemens Aktiengesellschaft | Hitzeschildelement für einen Verdichterluftbypass um die Brennkammer |
US10935235B2 (en) | 2016-11-10 | 2021-03-02 | Raytheon Technologies Corporation | Non-planar combustor liner panel for a gas turbine engine combustor |
US10935236B2 (en) * | 2016-11-10 | 2021-03-02 | Raytheon Technologies Corporation | Non-planar combustor liner panel for a gas turbine engine combustor |
US10655853B2 (en) | 2016-11-10 | 2020-05-19 | United Technologies Corporation | Combustor liner panel with non-linear circumferential edge for a gas turbine engine combustor |
US10830433B2 (en) | 2016-11-10 | 2020-11-10 | Raytheon Technologies Corporation | Axial non-linear interface for combustor liner panels in a gas turbine combustor |
US11719438B2 (en) | 2021-03-15 | 2023-08-08 | General Electric Company | Combustion liner |
Family Cites Families (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2928607B2 (ja) * | 1989-12-22 | 1999-08-03 | 株式会社日立製作所 | 燃焼装置及びその燃焼方法 |
UA27772C2 (uk) | 1990-11-29 | 2000-10-16 | Сіменс Аг | Теплозахисний екран на несучій структурі |
US6250082B1 (en) * | 1999-12-03 | 2001-06-26 | General Electric Company | Combustor rear facing step hot side contour method and apparatus |
EP1284390A1 (de) * | 2001-06-27 | 2003-02-19 | Siemens Aktiengesellschaft | Hitzeschildanordnung für eine Heissgas führende Komponente, insbesondere für Strukturteile von Gasturbinen |
EP1507116A1 (de) * | 2003-08-13 | 2005-02-16 | Siemens Aktiengesellschaft | Hitzeschildanordnung für eine ein Heissgas führende Komponente, insbesondere für eine Brennkammer einer Gasturbine |
US20100107645A1 (en) * | 2008-10-31 | 2010-05-06 | General Electric Company | Combustor liner cooling flow disseminator and related method |
US8359867B2 (en) * | 2010-04-08 | 2013-01-29 | General Electric Company | Combustor having a flow sleeve |
DE102012204103A1 (de) * | 2012-03-15 | 2013-09-19 | Siemens Aktiengesellschaft | Hitzeschildelement für einen Verdichterluftbypass um die Brennkammer |
DE102012204162A1 (de) * | 2012-03-16 | 2013-09-19 | Siemens Aktiengesellschaft | Ringbrennkammer-Bypass |
AU2013219140B2 (en) * | 2012-08-24 | 2015-10-08 | Ansaldo Energia Switzerland AG | Method for mixing a dilution air in a sequential combustion system of a gas turbine |
US9080447B2 (en) * | 2013-03-21 | 2015-07-14 | General Electric Company | Transition duct with divided upstream and downstream portions |
-
2015
- 2015-04-02 DE DE102015205975.8A patent/DE102015205975A1/de not_active Ceased
-
2016
- 2016-03-30 EP EP16713409.7A patent/EP3132202B1/de not_active Not-in-force
- 2016-03-30 WO PCT/EP2016/056881 patent/WO2016156370A1/de active Application Filing
- 2016-03-30 CN CN201680003016.5A patent/CN107076418A/zh active Pending
Also Published As
Publication number | Publication date |
---|---|
EP3132202B1 (de) | 2018-09-19 |
DE102015205975A1 (de) | 2016-10-06 |
CN107076418A (zh) | 2017-08-18 |
WO2016156370A1 (de) | 2016-10-06 |
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Inventor name: MALECHA, KASPAR MATTHIAS Inventor name: MOUJANE, YOUSSEF Inventor name: SCHILDMACHER, KAI-UWE Inventor name: BOETTCHER, ANDREAS Inventor name: KRIEGER, TOBIAS Inventor name: KLUGE, ANDRE |
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Inventor name: MOUJANE, YOUSSEF Inventor name: SCHILDMACHER, KAI-UWE Inventor name: KLUGE, ANDRE Inventor name: BOETTCHER, ANDREAS Inventor name: KRIEGER, TOBIAS Inventor name: MALECHA, KASPAR MATTHIAS |
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