CN1675502A - Gas turbine combustion chamber - Google Patents
Gas turbine combustion chamber Download PDFInfo
- Publication number
- CN1675502A CN1675502A CNA038188929A CN03818892A CN1675502A CN 1675502 A CN1675502 A CN 1675502A CN A038188929 A CNA038188929 A CN A038188929A CN 03818892 A CN03818892 A CN 03818892A CN 1675502 A CN1675502 A CN 1675502A
- Authority
- CN
- China
- Prior art keywords
- chamber
- combustion chamber
- manhole cover
- wall
- turbine
- 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
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
- F23M7/00—Doors
- F23M7/04—Cooling doors or door frames
-
- 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
Abstract
A gas turbine combustion chamber (4) comprises a manhole (27) as access to a combustion chamber interior (24), which may be sealed with a manhole cover (28). The manhole (27) comprises an inner cooling chamber and may thus take particularly high thermal loads.
Description
The present invention relates to a kind of gas-turbine combustion chamber, its have can seal by manhole cover, as entering the manhole of the inlet of combustion chamber inner chamber.
Use gas turbine drives generator or work mechanism in a lot of fields.Utilize this moment the interior turbine shaft that can make in the fuel to rotate.Combustion fuel in the combustion chamber will be imported in this combustion chamber by the air that air compressor compressed simultaneously for this reason.In the combustion chamber, flow through and be connected the turbine unit in downstream, described combustion chamber by the HTHP working media that combustion fuel produced, and in the there acting of expanding.
When this gas turbine of design, except reaching the certain power, its design object also comprises usually will realize extra high efficient.For the reason of thermokinetics aspect,, but promptly improve the temperature raising of implementation efficiency basically of from the combustion chamber, coming out and entering the working media of turbine unit by the raising outlet temperature.Therefore for this class gas turbine, people are devoted to realize and also can realize about 1200 ℃ to 1300 ℃ temperature always.
The combustion chamber of bearing high temperature like this when gas turbine is worked is for example for checking that purpose should enter for personnel.Disclose a kind of gas turbine that has the combustion chamber among Germany Patent document 199 24 607 A1, this combustion chamber has at least a portion zone that can check it by the inlet manhole.Disclose a kind of gas turbine that has toroidal combustion chamber in Germany Patent document 198 09 568 A1, wherein, be provided with inlet (manhole) in the flame chamber, personnel can enter the flame chamber by this manhole.But usually especially do not adopt the manhole that enters combustion chamber in up to 1200 ℃ to 1300 ℃ gas turbine, because such manhole may not bear the thermic load in the combustion chamber or can not guarantee the sealing of combustion chamber at least in ignition temperature.This point is particularly suited for being equipped with the combustion chamber liner, is the combustion chamber of so-called lining.Therefore, in order to allow personnel can enter the combustion chamber, need the dismantlement work of special trouble.
The object of the present invention is to provide a kind of gas-turbine combustion chamber, it can be applicable to the extra high gas turbine of ignition temperature, and personnel are entered wherein easily.
According to the present invention, above-mentioned purpose can realize by the gas-turbine combustion chamber with the described feature of claim 1.This gas-turbine combustion chamber has by manhole cover sealing, as the manhole that enters the inlet of combustion chamber inner chamber, wherein, described manhole cover has interior cooling chamber.Be somebody's turn to do interior cooling chamber, be that the interior cooling chamber of manhole cover can realize the cooling targetedly for the manhole cover of closed chamber's inner chamber.Therefore, this manhole cover also can be used under the high heat load situation of combustion chamber inner chamber, and unallowed excessive deformation can not occur, thereby can guarantee can both be sealed shut the combustion chamber inner chamber with this manhole cover under all running statuses.
Except manhole cover, preferred also the chamber wall in the zone of bearing extra high thermic load of gas-turbine combustion chamber at least carried out inside and cool off.At this, described chamber wall has so-called wall cooling chamber.The interior cooling chamber of preferred described manhole cover for example can be communicated with the wall cooling chamber of described chamber wall by interface channel.Thus can be easily at each the member place that surrounds described combustion chamber inner chamber, especially manhole cover and the chamber wall place that holds this manhole cover be formed up to look younger like heat condition.
According to a kind of preferred improvement design, can directly be communicated with the wall cooling chamber of described chamber wall especially simply by manhole cover being inserted the interior cooling chamber that makes described manhole cover in the described manhole.Especially can make the wall cooling chamber of described chamber wall not have cross section to carry out the transition in the interior cooling chamber of described manhole cover thus with dwindling.Preferably make the whole locular wall of described gas-turbine combustion chamber form uniform cooling chamber together with described manhole cover.
According to a kind of preferred design, the single cover of at least one of described manhole cover or the manhole cover lid liner of the interior cooling chamber of this manhole cover of sealing of described combustion chamber inner chamber (for example towards) towards described combustion chamber inner chamber the element that is fixed support, at this, described retaining element is fixed on a liner element adjacent with described manhole cover on the described chamber wall simultaneously.By the multi-functional of this retaining element, can farthest reduce the quantity of the retaining element in the combustion chamber.
The cross section of described retaining element is taken the shape of the letter U at least basically, and wherein, the first limit leg of this U-shaped retaining element supports the single cover of described manhole cover, and the another side leg of U-shaped retaining element then is fixed on described liner element on the chamber wall.Described retaining element preferably is trade shape on the whole.Both had enough stability and also had enough elasticity by retaining element being designed to the U-shaped rail.
Preferably be fixed on described retaining element on the chamber wall like this, promptly, portion's section of retaining element, especially U-shaped limit leg are stretched in the described manhole and will be supported on this place, and need not to unclamp retaining element and just manhole cover can be unloaded from manhole towards the lid liner of the manhole cover of combustion chamber inner chamber.The advantage of doing like this is, only need fix all once described liner element and lid liner are fixed on retaining element on described chamber wall or the manhole cover, and need not unload next retaining element personnel and just can enter the gas turbine combustion chamber through manhole.
Advantage of the present invention is that mainly because interior cooling chamber is set, manhole cover can bear high heat load, and can especially easily manhole cover be taken off from manhole together with cooling chamber in it.
By accompanying drawing one embodiment of the present invention is described in detail below, in the accompanying drawing:
Fig. 1 is the half sectional view of gas turbine;
Fig. 2 is the partial cross-section view of the combustion chamber of gas turbine shown in Figure 1.
In this two width of cloth accompanying drawing, identical member is represented with identical Reference numeral.
Gas turbine 1 shown in Figure 1 has compressor 2, combustion chamber or the gas-turbine combustion chamber 4 that combustion air is provided and is used for drive compression machine 2 and the not shown generator or the turbine 6 of work mechanism.For this reason, turbine 6 and compressor 2 are installed on the common turbine arbor 8 that is also referred to as turbine rotor.Generator or work mechanism also link to each other with described turbine arbor, and this turbine arbor is supported to can be around its central axis 9 rotations.
Combustion chamber 4 is equipped with some burners that are used for a burning liquid or gaseous fuel 10.Some liner elements 25 are equipped with also on the inwall of described combustion chamber or chamber wall 23, in addition.
Turbine 6 has some rotatable moving vanes 12 that link to each other with turbine spindle 8.Moving vane 12 is arranged on the turbine spindle 8 circlewise and therefore constitutes some moving vane groups.In addition, turbine 6 also comprises the guide vane 14 that some are fixing, and they are fixed on the inner housing 16 of turbine 6 equally in the form of a ring with surrounding the guide vane group.Moving vane 12 drives turbine arbor 8 at the momentum that this flows through the working media M of turbine 6 by transmission.14 of guide vanes are used for the flow direction of guiding working media M between per two moving vane groups that link to each other along the flow direction front and back of working media M or moving vane circle.The a pair of vane group that a circle guide vane 14 that is linked to each other by front and back or one group of guide vane and a circle moving vane 12 or one group of moving vane are formed is also referred to as turbine stage at this.
Each guide vane 14 has the platform 18 that is also referred to as blade root 19, and described platform is arranged on the inner housing 16 of turbine 6 as wall elements for fixing each guide vane 14.Comparatively speaking, platform 18 is the members that are subjected to heat-flash stream, because it constitutes the external boundary of the hot-gas channel of using for the working media M that flows through turbine 6.Each moving vane 12 is fixed on the turbine spindle 8 by the blade root 19 that is also referred to as platform 18 in a similar fashion, wherein, is supporting the moulding blade 20 that extends along axis of runner blade on the blade root 19 respectively.
Between the platform 18 of guide vane 14 spaces of two adjacent guide vane groups setting, there is a guide ring 21 to be set on the inner housing 16 of turbine 6 respectively.Stand to flow through the heat effect of the working media M of turbine 6 equally at the outer surface of this each guide ring 21, and these guide rings radially with the gap that is separated by, the outer end 22 of moving vane 12 on the other side.Be arranged on guide ring 21 between the adjacent guide vane group at this especially as closure element, it can avoid inwall 16 or other housing assembly parts to be subjected to flowing through the mistake thermic load of the thermodynamic medium M of turbine 6.
In order to realize higher efficient, gas turbine 1 is designed to can be used for the higher outlet temperature (that is from the combustion chamber the 4 working media M that flow out temperature) that is approximately 1200 ℃ to 1300 ℃.In order to realize this point, need chamber wall 23 is carried out the inside cooling.At this, combustion air and working media M (that is heat combustion flow) direction flow through at chamber wall 23 on the contrary and fixed thereon flow to burner 10 around the wall cooling chamber 26 that forms between the liner element 25 of combustion chamber inner chamber 24.Also heated simultaneously combustion air by this combustion chamber type of cooling with achieving one's goal.
Fig. 2 shows the chamber wall 23 that has manhole 27 in the mode of fragmentary section views, and manhole cover 28 is inserted in this manhole.Manhole cover 28 has parts of covering 29 and lid liner 30, and the described parts that cover are designed to be similar to chamber wall 23.Cover parts 29 and be also referred to as the interior cooling chamber 31 that crosses manhole cover 28 between the lid liner 30 of single cover.Correspondingly between chamber wall 23 and liner element 25 fixed thereon, also cross wall cooling chamber 26.The interior cooling chamber 31 of manhole cover 28 and the wall cooling chamber 26 of described chamber wall 23 are interconnected, and make described combustion air to flow perpendicular to the plane shown in the figure in the clear.
Cover parts 29 and have protuberance 33, utilize this protuberance the fixing of correspondence that covers parts insertion chamber wall 23 can be used in the indentation 34 at its edge.The basic configuration of manhole cover 28 is rectangular generally.For improving stability, cover parts 29 and chamber wall 23 in their join domain (that is in protuberance 33 and fixing zone) with indentation 34 towards combustion chamber inner chamber 24 progressive additives.Covering thickening or strengthen the zone and abutment face 36 being arranged in 35 of parts 28, lid liner 30 is resisted against on this abutment face with liner edge 37.Liner edge 37 links to each other with liner interarea 38 and is integral the ground warpage with it and forms.The liner edge 41 of liner element 25 is similarly reclining on the abutment face 39 of the enhancing of chamber wall 23 or buildup area 40.
Manhole cover 28 is supported by a unshowned fixture towards 42 ground, the outside, combustion chamber.Lid liner 30 supports with liner element 25 is designed to U type rail towards combustion chamber inner chamber 24 ground retaining element 43.At this, the first limit leg 44 of U type rail is resisted against on the liner edge 37 of manhole cover 28, and the second limit leg 45 of U type rail is resisted against on the liner edge 41 of liner element 31.Two limit legs of this of U type rail 44,45 are also referred to as portion's section of described retaining element 43.In order to support manhole cover 28, only need two retaining elements 43 generally towards combustion chamber inner chamber 24.These retaining elements 43 are fixed on the chamber wall by the bolt 46 of the thickened areas 40 that penetrates described chamber wall 23.
Bolt 46 spiral from combustion chamber inner chamber 24 is screwed in the chamber wall 23.Do not need described liner element 31 is implemented additional fastening on the zone 40 that thickens.Because the U type retaining element 43 that is fixed on the chamber wall 23 with bolt 46 not only is enough to liner element 25 is fixed on the chamber wall 23, and can support described lid liner 30 towards inner chamber 24 ground, described combustion chamber.The liner 25,30 that is also referred to as lining is by the sealing of retaining element 43 joint closes.In the zone of retaining element 43, stopped the effusion of cooling air.If there is the cooling air to select from wall cooling chamber 26 or interior cooling chamber 31 on liner edge 37 or mat edge 41, then the cooling air of Yi Chuing can be subjected to the obstruction of U type retaining element 43, thereby can not flow in the combustion chamber inner chamber 24.The cooling air that is blocked by U type retaining element 43 can flow to burner 10 along the retaining element 43 that is designed to track in the clear.
For manhole cover 28 is taken off from manhole 27, do not need to unload retaining element 43 or unclamp bolt 46.This point just can realize that by engaged configuration (Verhakungskonfiguration) by this engaged configuration, retaining element 43 supports to liner element 25 and lid liner 30 towards combustion chamber inner chamber 24.When being connected across 28 closed chamber 4 by manhole cover, retaining element 43 on the gap between the liner edge 41 of the liner edge 37 of manhole cover 28 and liner element 25, make thermodynamic medium M not flow out and flow to chamber wall 23 or cover on the parts 29 from combustion chamber inner chamber 24.Therefore, combustion chamber 4 all is added with liner all sidedly together with manhole cover 28.
Claims (7)
1. a gas-turbine combustion chamber (4), its have (a 28) sealing by manhole cover, as the manhole (27) that enters the inlet of combustion chamber inner chamber (24), it is characterized in that described manhole cover (28) has interior cooling chamber (31).
2. gas-turbine combustion chamber as claimed in claim 1 (4) is characterized in that, combustion chamber locular wall (23) has wall cooling chamber (26).
3. gas-turbine combustion chamber as claimed in claim 2 (4) is characterized in that, the interior cooling chamber (31) of described manhole cover (28) can be communicated with the wall cooling chamber (26) of described chamber wall (23).
4. gas-turbine combustion chamber as claimed in claim 3 (4), it is characterized in that the interior cooling chamber (31) of described manhole cover (28) inserts in the described manhole (27) by described manhole cover (28) and directly is communicated with the wall cooling chamber (26) of described chamber wall (23).
5. as each described gas-turbine combustion chamber (4) in the claim 2 to 4, it is characterized in that, be provided with a retaining element (43), at least one single cover (29,30) that this retaining element supports described manhole cover (28) makes it towards described combustion chamber inner chamber (24), simultaneously a liner element (25) adjacent with described manhole cover (28) is fixed on the described chamber wall (23).
6. gas-turbine combustion chamber as claimed in claim 5 (4), it is characterized in that, the cross section of described retaining element (43) takes the shape of the letter U at least basically, wherein, the first limit leg (44) of this U-shaped retaining element supports described single cover (29,30), and the another side leg (45) of this U-shaped retaining element is fixed described liner element (25).
7. as claim 5 or 6 described gas-turbine combustion chambers (4), it is characterized in that, a section (44,45) of described retaining element (43) stretches in the described manhole (27) like this, make that the lid liner (30) of described manhole cover (28) is supported (24) towards described combustion chamber inner chamber, and can take off described manhole cover (28) from described manhole (27).
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| EP02018489.1 | 2002-08-16 | ||
| EP02018489A EP1389714A1 (en) | 2002-08-16 | 2002-08-16 | Combustion chamber for gas turbine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN1675502A true CN1675502A (en) | 2005-09-28 |
| CN1318805C CN1318805C (en) | 2007-05-30 |
Family
ID=30470278
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNB038188929A Expired - Fee Related CN1318805C (en) | 2002-08-16 | 2003-08-01 | Gas turbine combustion chamber |
Country Status (6)
| Country | Link |
|---|---|
| US (1) | US20060037321A1 (en) |
| EP (2) | EP1389714A1 (en) |
| JP (1) | JP4167224B2 (en) |
| CN (1) | CN1318805C (en) |
| DE (1) | DE50309588D1 (en) |
| WO (1) | WO2004023042A1 (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107003000A (en) * | 2014-09-29 | 2017-08-01 | 西门子股份公司 | Heat insulating element for the heat shield of combustion chamber |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1398569A1 (en) * | 2002-09-13 | 2004-03-17 | Siemens Aktiengesellschaft | Gas turbine |
| EP1862740B1 (en) * | 2006-05-31 | 2015-09-16 | Siemens Aktiengesellschaft | Combustion chamber wall |
| EP2426321A1 (en) | 2010-09-03 | 2012-03-07 | Siemens Aktiengesellschaft | Casing for a gas turbine |
| US9534783B2 (en) | 2011-07-21 | 2017-01-03 | United Technologies Corporation | Insert adjacent to a heat shield element for a gas turbine engine combustor |
Family Cites Families (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB626249A (en) * | 1946-05-23 | 1949-07-12 | Babcock & Wilcox Ltd | Improvements in or relating to closure means for openings in walls of chambers arranged to contain gas under pressure |
| US4480436A (en) * | 1972-12-19 | 1984-11-06 | General Electric Company | Combustion chamber construction |
| US3978662A (en) * | 1975-04-28 | 1976-09-07 | General Electric Company | Cooling ring construction for combustion chambers |
| US4189352A (en) * | 1975-08-14 | 1980-02-19 | Krupp-Koppers, Gmbh | Coke oven door |
| US5333443A (en) * | 1993-02-08 | 1994-08-02 | General Electric Company | Seal assembly |
| DE19502730A1 (en) * | 1995-01-28 | 1996-08-01 | Abb Management Ag | Ceramic lining |
| US5782294A (en) * | 1995-12-18 | 1998-07-21 | United Technologies Corporation | Cooled liner apparatus |
| DE19809568A1 (en) | 1998-03-05 | 1999-08-19 | Siemens Ag | Ring-shaped combustion chamber arrangement |
| US6415724B1 (en) * | 1999-01-01 | 2002-07-09 | The Babcock & Wilcox Company | Water-jacketed, high-temperature, stretcher-accessible door for a boiler |
| DE19924607A1 (en) | 1999-05-28 | 2000-11-30 | Siemens Ag | Inspection device for an annular combustion chamber of a gas turbine and method for inspecting an annular combustion chamber of a gas turbine |
-
2002
- 2002-08-16 EP EP02018489A patent/EP1389714A1/en not_active Withdrawn
-
2003
- 2003-08-01 US US10/524,523 patent/US20060037321A1/en not_active Abandoned
- 2003-08-01 DE DE50309588T patent/DE50309588D1/en not_active Expired - Lifetime
- 2003-08-01 WO PCT/EP2003/008548 patent/WO2004023042A1/en active IP Right Grant
- 2003-08-01 CN CNB038188929A patent/CN1318805C/en not_active Expired - Fee Related
- 2003-08-01 JP JP2004533306A patent/JP4167224B2/en not_active Expired - Fee Related
- 2003-08-01 EP EP03753347A patent/EP1529181B1/en not_active Expired - Lifetime
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107003000A (en) * | 2014-09-29 | 2017-08-01 | 西门子股份公司 | Heat insulating element for the heat shield of combustion chamber |
Also Published As
| Publication number | Publication date |
|---|---|
| JP4167224B2 (en) | 2008-10-15 |
| EP1529181B1 (en) | 2008-04-09 |
| DE50309588D1 (en) | 2008-05-21 |
| US20060037321A1 (en) | 2006-02-23 |
| JP2005535867A (en) | 2005-11-24 |
| CN1318805C (en) | 2007-05-30 |
| EP1389714A1 (en) | 2004-02-18 |
| EP1529181A1 (en) | 2005-05-11 |
| WO2004023042A1 (en) | 2004-03-18 |
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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: 20070530 Termination date: 20160801 |