CN104169649B - Toroidal combustion chamber by-pass collar - Google Patents
Toroidal combustion chamber by-pass collar Download PDFInfo
- Publication number
- CN104169649B CN104169649B CN201380013443.8A CN201380013443A CN104169649B CN 104169649 B CN104169649 B CN 104169649B CN 201380013443 A CN201380013443 A CN 201380013443A CN 104169649 B CN104169649 B CN 104169649B
- Authority
- CN
- China
- Prior art keywords
- combustion chamber
- toroidal combustion
- shell
- shield plate
- toroidal
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
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
- F23R3/26—Controlling the air flow
-
- 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
- F23R3/08—Arrangement of apertures along the flame tube between annular flame tube sections, e.g. flame tubes with telescopic sections
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)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The present invention relates to a kind of toroidal combustion chamber for combustion gas turbine (1), described toroidal combustion chamber has shell (12), described shell has at least one for the import (4) of burner (3) and the outlet (7) led in turbine chamber (8), it is characterized in that, in the region of described outlet (7), the passage (14) of that close and basic axis of symmetry (2) parallel orientation with described toroidal combustion chamber (1) it is provided with in described shell (12), compressed air can be through described passage (14) and introduce described toroidal combustion chamber (1).The invention still further relates to a kind of combustion gas turbine.
Description
Technical field
The present invention relates to a kind of toroidal combustion chamber with by-pass collar, for subtracting when sub-load operates
The discharge of few carbon monoxide and a kind of combustion gas turbine with this toroidal combustion chamber.
Background technology
When the sub-load of combustion gas turbine operates, the ignition temperature in combustor declines.Thus,
Also below minimum is dropped in the preliminary area temperature relevant to carbon monoxide emission, thus the oxygen strengthened
Change generation or the discharge of carbon.Because avoiding this situation, so the available part of combustion gas turbine
Load range is limited.
Summary of the invention
The technical problem to be solved is to provide the toroidal combustion chamber of a kind of aforementioned type, and it can
To significantly increase available partial load region.
Described technical problem is addressed by a kind of toroidal combustion chamber, wherein specifies, this for combustion gas
The chlamydate toroidal combustion chamber of tool of turbine, described shell has at least one import for burner
With the outlet led in turbine chamber, it is characterised in that set in the region of described outlet in the housing
It is equipped with the passage of that can close and the basic axis of symmetry parallel orientation with described toroidal combustion chamber, compression sky
Gas can be through described passage and introduce described toroidal combustion chamber.
By this measure, compressed air can be imported in the end regions of combustor, and without participating in combustion
Burning, say, that after combustion process terminates, compressed air results in air fuel again and mixes
Compound.This result caused is, more oxygen-enriched mixture can be at combustion chamber in the case of higher temperature
Interior burned, and in sub-load operates, thus reduce carbon monoxide emission.
In a preferred embodiment, in described annular in toroidal combustion chamber is included in the region of described outlet
The last string heat shield plate that the most circumferentially disposes in the inside of combustor and along described extremely
The direction of a few import and the row heat shield plate second from the bottom of described last string arranged adjacent, wherein,
It is provided with in the region of described passage between the last string and row second from the bottom of described heat shield plate
Gap.By this gap, compressed air can be uninterruptedly in flowing in combustion chamber.
It is also advantageous that, in order to close and open described passage, the outside of described shell is provided with bag
Containing the adjusting means of some ring segment, described ring segment constitutes a ring, and described ring is same with described toroidal combustion chamber
Axle orients and can move axially relative to described toroidal combustion chamber.It is simple that ring segment has assembly and disassembly
Advantage.
At this desirably, the ring of adjusting means can move without polar region, in order to regulation is wished as required
The gap length hoped, and thus the air capacity determined can be taken out before combustion from compressed air.
In the advantageous embodiment of the present invention, described ring segment has use in its side deviating from turbine
In the projection embedding described passage.At this desirably, described projection is designed to trapezoidal.Convex by this
Rise, particularly by its trapezoidal shape so that particularly accurately regulated by the air capacity of channel lead.
Passage is it is of course possible to be completely enclosed.Here, ring is moved only in the axial direction by mechanical mechanism.This for
Control and the mechanical mechanism of shift(ing) ring has different probabilities.Thus, this mechanical mechanism can be motor,
Leverage, hydraulic mechanism etc., its such as make ring track or other move and slide axially on element.Root
According to selection, this mechanical mechanism can also be arranged on housing interiorly or exteriorly.
At relatively high temperatures in the case of operation toroidal combustion chamber advantageously, the projection of ring segment is born at it
On the surface of the steam of burning, there is thermal insulation layer (TBC).The most desirably, outside described
The inside of shell between the heat shield plate of last string and row second from the bottom, namely at passage to combustor
In the region in the interior gap between opening, there is thermal insulation layer.At the toroidal combustion chamber according to prior art
In, the heat shield plate of last string and row second from the bottom adjoins each other, and heat shielding is passed through in the inside of shell
Shield plate is intactly protected.By according to the gap existing for the present invention, shell in this region more strongly
Bear the steam of burning.
It is also suitable that, the last string heat that the nucleus of distance burning is farthest in all heat shield plates
Barricade is metal, and row second from the bottom are ceramic, because the work temperature of one side ceramic material
Spend the maximum operation temperature significantly more than high-fire resistance metal alloy, and on the other hand high-fire resistance metal
Alloy has relatively low fragility and preferable heat conduction and guide temp.
The last present invention also provides for a kind of novel combustion gas being integrated with the toroidal combustion chamber according to the present invention
Turbine.
By according to the present invention can the adjusting means of electrodeless regulation, it is for the stub area at combustor
In, import compressed air the most after being combusted, thus in sub-load operates, reduce carbon monoxide
Discharge because owing to more oxygen-enriched mixed gas makes ignition temperature be conditioned get Geng Gao.
Unlike current design, it is no longer necessary to when base load operates cool down air.
Additionally, the present invention can be realized, because ring segment, such as two semi-rings are simple by relatively simple
Component, it only needs to move axially.
Accompanying drawing explanation
The present invention is expanded on further in conjunction with accompanying drawing.Schematically in the figures and not to scale:
Fig. 1 illustrates the combustion system with the toroidal combustion chamber according to the present invention,
Fig. 2 illustrates the side towards turbine of toroidal combustion chamber, has the tune on shell and bypass pipe
Regulating device,
Fig. 3 illustrates the semi-ring of the adjusting means for by-pass collar,
Fig. 4 illustrates the heat shield plate of the metal according to prior art,
Fig. 5 illustrates the heat shield plate of the metal for the toroidal combustion chamber according to the present invention, and
The inner side of the toroidal combustion chamber that Fig. 6 is shown in exit region.
Detailed description of the invention
Fig. 1 schematically and is exemplarily illustrated the combustion system of the toroidal combustion chamber 1 according to the present invention.Ring
Shape combustor 1 is made up of the ring of the closing disposed around rotation axis 2.Burner 3 is at combustor 1
It is placed in upper area in import 4.There, fuel 5 mixes with compressed air 6 phase.In burning
The burning of self is realized in room 1.The burning gases of heat, through outlet 7 entrance turbine chamber 8, burn at this
Gas and the first blade 9 contact.In order to protect before ignition, toroidal combustion chamber 1 is lined with pottery
The heat shielding 10 of porcelain and the heat shielding 11 of metal, they are fixed on shell 12.
According to the present invention, combustor outer casing 12 in the region of outlet 7 in the heat shielding of last pottery
Set between the import coverboard (i.e. last string heat shielding 11) of row 13 (row heat shielding the most second from the bottom) and metal
Being equipped with passage 14, this passage 14 is arranged essentially parallel to the axis 2 of toroidal combustion chamber and orients.
Thus, this passage 14 can be closed the most as required and open, and it is in the outside of shell 12
It is provided with adjusting means 15, as shown in Figure 2.Adjusting means 15 have some ring segment 16, such as two
Semi-ring, as shown in Figure 3.The gap of determination in passage 14 can be regulated big by corresponding protruding 17
Little, or completely enclosed passage 14.
In order to make gas can flow into toroidal combustion chamber 1, the import coverboard of metal, the most last heat
The plate of shielding row 11 is contracted relative to the last string heat shield plate 18 of toroidal combustion chamber of the prior art
Short.Fig. 4 illustrates the last string heat shield plate 18 of this toroidal combustion chamber of the prior art, and edge
Dotted line shortens, thus obtain shown in Fig. 5, be also the metal fever barricade 11 required for the present invention.
Fig. 6 illustrates the inner side view of toroidal combustion chamber 1, and it has last string 11 and row second from the bottom
The heat shield plate of 13 and for the passage 14 in the shell 12 of gas bypass when sub-load operates
Opening 20.
Because according to the present invention, the last string 11 of heat shield plate is relative to heat shielding of the prior art
Plate is shortened and so disposes on the shell 12 of toroidal combustion chamber 1 so that last string need not be straight
Adjoining being connected on row heat shield plate 13 second from the bottom, the most annularly the circumference of combustor 1 forms one
There is no the gap 19 of the most that solar heat protection.In this gap 19, passage 14 is in toroidal combustion chamber 1
Portion is open.Shell 12 between opening 20 bears high temperature when toroidal combustion chamber 1 runs.
Even if in order to shell 12 being protected for this temperature in the case of there is gap 19, shell 12
Gap 19 between last string 11 and the heat shield plate of row second from the bottom 13, the inside in the range of,
Namely between the opening 20 towards combustion chamber of passage 14, it is provided with thermal insulation layer.
The projection 17 of ring segment 16 also has thermal insulation layer on the surface of its steam bearing burning.
Claims (9)
1. the toroidal combustion chamber (1) for combustion gas turbine, described toroidal combustion chamber has shell
(12), described shell has at least one and for the import (4) of burner (3) and leads to going out in turbine chamber (8)
Mouth (7), it is characterised in that be provided with envelope in described shell (12) in the region of described outlet (7)
The passage (14) of that close and with described toroidal combustion chamber (1) axis of symmetry (2) parallel orientation, compressed air can be worn
Cross described passage (14) and introduce described toroidal combustion chamber (1), and, in order to close and open described passage
(14), the adjusting means (15) comprising some ring segment (16) it is provided with in the outside of described shell (12), described
Ring segment (16) constitutes a ring, and described ring is coaxial with described toroidal combustion chamber (1) to be oriented and relative to described
Toroidal combustion chamber (1) can move axially.
2. toroidal combustion chamber (1) as claimed in claim 1, it is included in the region of described outlet (7)
The last string heat circumferentially disposed on described shell (12) in the inside of described toroidal combustion chamber (1)
Barricade (11) and along the direction of described at least one import (4) and described last string heat shield plate (11) phase
The adjacent row heat shield plate (13) second from the bottom disposed, wherein, described last string heat shield plate (11) and
It is passed through internal the opening of described toroidal combustion chamber (1) at described passage (14) between number secondary series heat shield plate (13)
It is provided with gap (19) in the region of mouth (20).
3. toroidal combustion chamber (1) as claimed in claim 1, wherein, described ring can move without polar region.
4. toroidal combustion chamber (1) as claimed any one in claims 1 to 3, wherein, described ring segment
(16) there is the projection (17) for embedding described passage (14) in its side deviating from turbine.
5. toroidal combustion chamber (1) as claimed in claim 4, wherein, described projection (17) is designed to ladder
Shape.
6. toroidal combustion chamber (1) as claimed in claim 4, wherein, described projection (17) is bearing steam
Surface on there is thermal insulation layer.
7. toroidal combustion chamber (1) as claimed in claim 2, wherein, the inside of described shell (12) is in institute
In stating the region of gap (19), there is thermal insulation layer.
8. toroidal combustion chamber (1) as claimed in claim 2, wherein, described last string heat shield plate
It is metal, and described row heat shield plate second from the bottom is ceramic.
9. the combustion gas turbine of the toroidal combustion chamber having as described in one of aforementioned claim (1).
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE102012204162.1 | 2012-03-16 | ||
| DE102012204162A DE102012204162A1 (en) | 2012-03-16 | 2012-03-16 | Ring combustor bypass |
| PCT/EP2013/055344 WO2013135859A2 (en) | 2012-03-16 | 2013-03-15 | Annular-combustion-chamber bypass |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104169649A CN104169649A (en) | 2014-11-26 |
| CN104169649B true CN104169649B (en) | 2016-11-09 |
Family
ID=47901090
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201380013443.8A Expired - Fee Related CN104169649B (en) | 2012-03-16 | 2013-03-15 | Toroidal combustion chamber by-pass collar |
Country Status (6)
| Country | Link |
|---|---|
| US (1) | US20150007573A1 (en) |
| EP (1) | EP2812636B1 (en) |
| KR (1) | KR20140138710A (en) |
| CN (1) | CN104169649B (en) |
| DE (1) | DE102012204162A1 (en) |
| WO (1) | WO2013135859A2 (en) |
Families Citing this family (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104807043A (en) * | 2014-11-29 | 2015-07-29 | 哈尔滨广瀚燃气轮机有限公司 | Annular combustion chamber of natural gas fuel gas turbine |
| CN104566463B (en) * | 2014-11-29 | 2016-12-07 | 哈尔滨广瀚燃气轮机有限公司 | Gas turbine low discharging burning chamber conditioner |
| DE102015202097A1 (en) * | 2015-02-06 | 2016-08-11 | Siemens Aktiengesellschaft | Ring combustion chamber with bypass segment |
| DE102015205975A1 (en) * | 2015-04-02 | 2016-10-06 | Siemens Aktiengesellschaft | Umführungs heat shield element |
| DE102015215207A1 (en) * | 2015-08-10 | 2017-02-16 | Siemens Aktiengesellschaft | Combustion chamber for a gas turbine and heat shield element for lining such a combustion chamber |
| WO2017032424A1 (en) * | 2015-08-27 | 2017-03-02 | Siemens Aktiengesellschaft | Metal heat shield element with an optimized cooling air function |
| CN108131399B (en) * | 2017-11-20 | 2019-06-28 | 北京动力机械研究所 | A kind of engine bearing seat cooling structure |
| EP3499125A1 (en) * | 2017-12-12 | 2019-06-19 | Siemens Aktiengesellschaft | Pipe combustion chamber with ceramic cladding |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5557920A (en) * | 1993-12-22 | 1996-09-24 | Westinghouse Electric Corporation | Combustor bypass system for a gas turbine |
| US6546627B1 (en) * | 2000-09-14 | 2003-04-15 | Hitachi, Ltd. | Repair method for a gas turbine |
| CN101839482A (en) * | 2009-03-20 | 2010-09-22 | 通用电气公司 | The system and method that is used for reintroducing gas turbine combustion bypass flow |
| EP2423596A1 (en) * | 2010-08-27 | 2012-02-29 | Siemens Aktiengesellschaft | Heat shield element |
Family Cites Families (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3958413A (en) * | 1974-09-03 | 1976-05-25 | General Motors Corporation | Combustion method and apparatus |
| US5636510A (en) * | 1994-05-25 | 1997-06-10 | Westinghouse Electric Corporation | Gas turbine topping combustor |
| JP2002317650A (en) * | 2001-04-24 | 2002-10-31 | Mitsubishi Heavy Ind Ltd | Gas turbine combustor |
| SE523082C2 (en) * | 2001-11-20 | 2004-03-23 | Volvo Aero Corp | Device at a combustion chamber of a gas turbine for controlling gas inflow to the combustion zone of the combustion chamber |
| US7631504B2 (en) * | 2006-02-21 | 2009-12-15 | General Electric Company | Methods and apparatus for assembling gas turbine engines |
| US20110225947A1 (en) * | 2010-03-17 | 2011-09-22 | Benjamin Paul Lacy | System and methods for altering air flow in a combustor |
| GB201200237D0 (en) * | 2012-01-09 | 2012-02-22 | Rolls Royce Plc | A combustor for a gas turbine engine |
| DE102012204103A1 (en) * | 2012-03-15 | 2013-09-19 | Siemens Aktiengesellschaft | Heat shield element for a compressor air bypass around the combustion chamber |
-
2012
- 2012-03-16 DE DE102012204162A patent/DE102012204162A1/en not_active Ceased
-
2013
- 2013-03-15 CN CN201380013443.8A patent/CN104169649B/en not_active Expired - Fee Related
- 2013-03-15 WO PCT/EP2013/055344 patent/WO2013135859A2/en active Application Filing
- 2013-03-15 US US14/382,918 patent/US20150007573A1/en not_active Abandoned
- 2013-03-15 EP EP13710388.3A patent/EP2812636B1/en not_active Not-in-force
- 2013-03-15 KR KR1020147025333A patent/KR20140138710A/en not_active Application Discontinuation
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5557920A (en) * | 1993-12-22 | 1996-09-24 | Westinghouse Electric Corporation | Combustor bypass system for a gas turbine |
| US6546627B1 (en) * | 2000-09-14 | 2003-04-15 | Hitachi, Ltd. | Repair method for a gas turbine |
| CN101839482A (en) * | 2009-03-20 | 2010-09-22 | 通用电气公司 | The system and method that is used for reintroducing gas turbine combustion bypass flow |
| EP2423596A1 (en) * | 2010-08-27 | 2012-02-29 | Siemens Aktiengesellschaft | Heat shield element |
Also Published As
| Publication number | Publication date |
|---|---|
| US20150007573A1 (en) | 2015-01-08 |
| DE102012204162A1 (en) | 2013-09-19 |
| EP2812636A2 (en) | 2014-12-17 |
| WO2013135859A2 (en) | 2013-09-19 |
| KR20140138710A (en) | 2014-12-04 |
| EP2812636B1 (en) | 2016-06-29 |
| WO2013135859A3 (en) | 2013-11-14 |
| CN104169649A (en) | 2014-11-26 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20161109 Termination date: 20170315 |