CN101855497A - Support ring for heat shield elements on aflame tube and a combustion chamber arrangement with said support ring - Google Patents

Support ring for heat shield elements on aflame tube and a combustion chamber arrangement with said support ring Download PDF

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Publication number
CN101855497A
CN101855497A CN200880113262A CN200880113262A CN101855497A CN 101855497 A CN101855497 A CN 101855497A CN 200880113262 A CN200880113262 A CN 200880113262A CN 200880113262 A CN200880113262 A CN 200880113262A CN 101855497 A CN101855497 A CN 101855497A
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CN
China
Prior art keywords
support ring
buttress
cell wall
fire tube
groove
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
CN200880113262A
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Chinese (zh)
Other versions
CN101855497B (en
Inventor
埃尔克·亨舍尔
米兰·施马尔
马丁·斯塔珀
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Siemens Energy Global GmbH and Co KG
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Siemens AG
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Publication date
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Publication of CN101855497A publication Critical patent/CN101855497A/en
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Publication of CN101855497B publication Critical patent/CN101855497B/en
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    • 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
    • F23R3/42—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
    • 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
    • F23M2900/00—Special features of, or arrangements for combustion chambers
    • F23M2900/05002—Means for accommodate thermal expansion of the wall liner
    • 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

Abstract

A support ring (113) for heat shield elements (111) o a flame tube (101) is disclosed, wherein at least one groove (119) on the outer side (115) of the support ring. The groove (119) has a groove wall (125) running at an angel with relation to the radial direction of the support ring (113). A combustion chamber arrangement with said support is also disclosed.

Description

Be used for the support ring of fire tube heat shield element and with the combusting room device of this support ring
Technical field
The present invention relates to a kind ofly to be used for fire tube, in particular for the support ring of the heat shield element of the fire tube of gas turbine.In addition, the present invention relates to a kind of combusting room device that has fire tube and mixing chamber, this device especially is applied in the gas turbine.
Background technology
The support ring of heat shield element, can have the groove that extends in its outside as the support ring that especially is applied in the heat shield element in the gas turbine fire tube, this groove is as cold air channel.Cross section of pressing the support ring of prior art shown in Figure 1, wherein, described support ring is accepted by the buttress edge (Zinnenkranz) of mixing chamber.The figure shows the cross section of support ring 1 and the buttress 3 that mixing chamber has been shown in the viewgraph of cross-section of signal.Support ring has strengthening region 5, and this zone is equipped with all whole peripheral surface of extend past support ring of inside groove 7 and 9, two grooves of water jacket again.Water jacket 9 and inside groove 7 are interconnected on fluid technique by a plurality of radial direction through hole 11.Water jacket 9 is formed for the fresh air conveying passage of cooled supports ring 1.Then, fresh air feeds inside, combustion chamber by hole 11.In addition, strengthening region 5 forms the flange shape projection that projects into inside, combustion chamber, and this projection forms the carrier of heat shield element.
Because support ring 1 and pile up neatly 3 different thermal coefficient of expansions, the temperature in the running of gas turbine causes piling up neatly 3 and reins in the support ring 1 in the gas turbine operation process.Rein in into result afterwards shown in Figure 2.Because fret wear is formed with projection 13 in buttress 3, this projection is reined in the water jacket 9 of support ring 1.Now, if close gas turbine, support ring 1 because different thermal coefficient of expansions differently shrinks, makes support ring 1 apply power F with buttress 3 on buttress 3 Fl, on support ring, apply power F and pile up neatly 3 MiThese power cause support ring 1 and buttress to snap in each other, wherein occur very large power in cooling procedure, if pile up neatly 3 or untimely repairing of support ring or replacing, described power can cause serious consequence.Therefore, regularly the transitional region between mixing chamber and the fire tube to be checked that wherein, the time interval between twice inspection is determined by described reining in into process.
Summary of the invention
Technical problem to be solved by this invention is, a kind of favourable support ring and a kind of favourable combusting room device are provided, and it especially can prolong the service intervals of the transition region between fire tube and the mixing chamber.
This technical problem solves by the support ring of described by claim 1, as to be used for fire tube heat shield element and described by claim 7, as to have fire tube and mixing chamber combusting room device.Each dependent claims comprises the various favourable designs of the present invention.
The heat shield element that is used for fire tube, especially gas turbine fire tube, have at least one groove by the outside of support ring of the present invention.This groove has the cell wall with respect to the radial skew extension of support ring.The appropriate angle radially of the relative support ring of surface normal of the cell wall that tilts to extend is in 30 ° to 60 ° scope.
The cell wall that tilts to extend causes forming the projection of wedge shape in buttress when the buttress edge of mixing chamber is reined in into support ring.This projection has and the corresponding lozenges of oblique cell wall.Now, if close gas turbine, because the mixing chamber thermal coefficient of expansion different with support ring occurs along the power of the axial action of support ring, the inclined-plane causes producing the power along the radial effect of support ring, and this power makes buttress separate with support ring.Therefore, especially avoided because the wearing and tearing of the buttress that causes along support ring axial excessive power.
Through hole especially can be in the zone of groove, and this through hole extends to its inboard from the outside of support ring, and as the cold air opening that is used for the cooled supports ring and is used to discharge the cold air of introducing by groove.In the time of in piling up neatly the groove of in depth reining at support ring, interrupt the conveying of fresh air for avoiding groove, the cell wall relative with oblique cell wall can have nonplanar geometry.It especially can form along the plane of the axial bending of support ring.
In order to reduce to rein in the material unaccounted-for (MUF) in the fashionable support ring outside and slow down thus and rein in into process, its outside can have coating, just anti abrasive layer (hard protective surface, wearing layer).
Have fire tube and mixing chamber by combusting room device of the present invention.This combusting room device especially can be applied in the gas turbine.Fire tube has the output that has the support ring that is used for heat shield element, especially ceramic heat shield element.Mixing chamber has the edge that has outstanding buttress, and wherein, described buttress is formed for accepting the carrier of support ring.In pressing combusting room device of the present invention, support ring is designed to by support ring of the present invention.Therefore, at also can in by combustion chamber of the present invention, obtaining by described effect of support ring of the present invention and advantage, the effect that therefore can the reference support ring and the explanation of advantage.
For slow down rein in into, except the outside of support ring, the buttress the inboard also can have coating.The coating of buttress especially can be harder than the coating of support ring.Certainly, described coating also can be the same, and perhaps the coating of support ring can be harder.Yet the coating of preferred buttress is harder than the coating of support ring, needs less expense because the maintenance of support ring or replacing are compared the maintenance of buttress and changed.In addition, when coating is identical the wearing and tearing of buttress than the easier generation of damage of support ring, and more serious for gas turbine.Therefore, can be by selecting the thickness of coating rightly, the wearing and tearing on control support ring and the buttress distribute.
Description of drawings
Explanation to form of implementation draws other feature, characteristic and advantage of the present invention with reference to accompanying drawing by following.
Fig. 1 shows the cross section of support ring in the buttress edge according to prior art,
Fig. 2 shows at the buttress edge that causes owing to operation and reins in into the cross section shown in Figure 1 after the support ring,
Fig. 3 shows the combusting room device that has fire tube and mixing chamber according to of the present invention in the diagram,
Fig. 4 is in the cross section that there is shown the transition region between fire tube and the mixing chamber of analysing and observe of amplifying,
Fig. 5 shows along the profile of the line V-V among Fig. 4,
Fig. 6 show operation cause rein in into after support ring and the buttress of mixing chamber,
Fig. 7 shows the figure of the power that occurs when combusting room device cools off.
The specific embodiment
The following explanation with reference to Fig. 3 to Fig. 7 pressed combusting room device of the present invention, and it has by support ring of the present invention, that be used for heat shield element, is also referred to as the base support ring.Current form of implementation shows a kind of combusting room device, wherein vertically is provided with fire tube, that is to say the axially vertically extension of fire tube.Accordingly, fire tube radially is horizontal direction.Vertically the hot combustion gas of flowing out from fire tube is deflected into the flow direction of a level by mixing chamber.
Fig. 3 there is shown described combusting room device analysing and observe, and it has the fire tube 101 that has burner end 103 and output 105, is provided with (unshowned) burner at this burner end, and the hot combustion gas that produces in the combustion chamber is flowed out from this output.Fire tube 101 inserts the bearing 109 of mixing chamber 107 with its output 105.Mixing chamber will be passed to (unshowned) turbine from the hot combustion gas that fire tube 101 flows out.
The inside of fire tube 101 is equipped with ceramic heat shield element, is also referred to as heat shielding stone, so that the protection chamber wall is not influenced by corrosive hot combustion gas.The base support ring 113 of stationary heat shielding stone 111 is arranged on the output of fire tube 101, and wherein, major part is arranged in the carrier 109 of mixing chamber 107.Carrier 109 and base support ring 113 illustrate enlargedly in the cross section mode in Fig. 4.
Base support ring 113 has the outside 115 and inboard 117.115 and inboard 117 all exist groove 119,121, the whole circumference of described groove extend past base support ring 113 in the outside.In addition, the outside of base support ring 113 is equipped with the coating 129 that reduces to wear and tear.Several through holes 123 are distributed in the circumference of base support ring 113 with the spacing of rule, and described through hole is communicated with the groove 121 (hereinafter referred to as inner groovy 121) of design in inboard 117 groove in the outside 117 119 (hereinafter referred to as outer groove 119) on flow technique.Outer groove 119 is as cold air channel, and it realizes the distribution of cold air around base support ring 113.Then, cold air can arrive inner groovy 121 by through hole 123 from outer groove 119, and enters inside, combustion chamber from this.Outer groove 117 and inner groovy 121 are arranged on the flange shape projection 122, the radially inner projection towards the combustion chamber of this projection.The upside 124 of projection 122 is formed for descending most the supporting surface (see figure 3) of row's heat shield element 111.
The outer groove 119 of base support ring 113 has the cell wall 125 of the radial skew of relative base support ring 113.The surface normal of the cell wall 125 that tilts and support ring 113 radially become an angle between 30 ° to 60 °.In current form of implementation, this angle is about 45 °.The cell wall 127 relative with the cell wall that tilts 125 has nonplanar geometry, and in current form of implementation along the axial bending of support ring 113.
Fig. 5 shows along the cutaway view of the base support ring 113 of the line V-V among Fig. 4.As shown in the figure, through hole 123 is along the radially extension of support ring 113, but along peripheral, oblique, and with radially into about 60 ° angle.
The base support ring 113 of fire tube 101 is inserted in the carrier 109 of mixing chamber 107.This carrier 109 is formed by the buttress 133 in the wall 131 that is configured in mixing chamber.At this, the buttress 133 wall sections by mixing chamber form, and this wall section is circumferentially run through around mixing chamber grooves distributed or depression by the edge.These grooves or depression be extending axially the circumferential wall along flange basically from the edge of circumferential wall.Therefore, the wall section that does not set groove or depression of described carrier 109 relative mixing chambers 107 has increased flexibility, therefore the power that can occur between mixing chamber 107 and fire tube 101 in certain degree compensation.
The inboard 135 of buttress 133 is planes, and is equipped with coating 137.In current form of implementation, the coating 137 of buttress is harder than the coating 129 in the outside 115 of base support ring 113, and the wearing and tearing major part that occurs, produce owing to the friction of base support ring 113 in the inboard of buttress 133 that therefore is in operation concentrates on the base support ring 113.
Fig. 6 shows the base support ring 113 when combusting room device reaches definite service life and the cross section of carrier 109.If do not carry out prior detection and replacing or maintenance, be in operation, the buttress edge of mixing chamber 107 is reined in the base support ring 113 into fire tube 101.Fig. 6 shows this state.Because rein in buttress 133 and formed projection 139, this projection projects into outer groove 119, just in the cooling duct.This projection 139 is owing to wearing and tearing have and the almost parallel prism 141 of cell wall 125 that tilts.
If fire tube 101 and mixing chamber 107 coolings after gas turbine cuts out the power F of effect vertically just occurs so between the inclination cell wall 125 of the inclined side 141 of projection 139 and support ring 113 MiAnd F Fl, described power is produced by the axial relative motion of two parts that produce when cooling off.By reining in fashionable because cell wall 125 wedge-type shapes that produce, projection 139 that tilt, at support ring 113 with pile up neatly and produce counteractive radial load (level) between 133, this power is squeezed these parts mutually and is opened, thereby and is separated from each other.The wearing and tearing of having avoided buttress to take place thus owing to too high axial force.Cause contact-making surface at the prism 141 of reining in fashionable generation in the cell wall 125 that tilts and the projection 139 of buttress with respect to the radial and axial inclination of two parts, it utilizes in this wise or transforms when variations in temperature because the power that the transient motion of parts produces, make parts automatically unclamp mutually, just remove mutually, and the power that is occurred can not cause the consequence of failure such as wearing and tearing, distortion as buttress.Fig. 7 shows one to try hard to, and it shows because the power F that transient motion causes TransientBe applied to the power F that produces on the fire tube Result.F1And act on power F on the mixing chamber Result.Mi
In addition, the curved side 127 of the outer groove 119 in the base support ring 113 causes, even if cold air channel enough big, that be used for the base support ring is also arranged in the dark outer groove 119 that embeds base support rings 113 of noticeable wear and associated therewith, buttress 133 time always.Therefore can avoid the obstruction of cold air channel.
Although in current form of implementation, avoid the obstruction of cold air channel by cell wall 125 relative cell wall 127 bendings that make and tilt, the nonplanar geometry of other of this cell wall also can cause same result, as cell wall being configured to the roof shape, just have two wall sections that are in the plane of angle of intersection.Under the simplest situation can by be provided with in 115 in its outside cross section rectangular, radially at angle the groove of base support ring 113 is realized relatively.Groove and the angle that radially becomes at this preferably in 30 ° to 60 ° scope.For fear of stopping up cooling air channels because buttress (owing to operation more of a specified duration) deeper embeds, this cooling air channels can exceed possible embedding buttress and be configured in the support ring to heavens.
According to the present invention, the base support ring also in the zone of (supply cold air) groove, be equipped with the inclined-plane (for example 40 °, but its variable pitch and select according to the function needs), it causes the imposed deformation of mixing chamber and base support ring when parts cool off.Distortion by " wedge " has produced (level) reaction force in support ring and mixing chamber, described power " is separated these parts ".Therefore avoided buttress owing to too high vertical force is worn and torn.

Claims (9)

1. support ring (113) that is used for the heat shield element (111) of fire tube (101), wherein, there is at least one groove (119) in the outside (115) at described support ring, it is characterized in that described groove (119) has the cell wall (125) with respect to the radial skew extension of described support ring (113).
2. support ring as claimed in claim 1 (113) is characterized in that, the described relatively support ring of surface normal (113) of the cell wall (125) that described inclination is extended radially become an angle in 30 ° to 60 ° scopes.
3. support ring as claimed in claim 1 or 2 (113) is characterized in that, some through holes (123) are arranged in the zone of described groove (125), and described through hole extends to the inboard (117) of described support ring from the outside (115) of described support ring (113).
4. support ring as claimed in claim 3 (113) is characterized in that, the cell wall (127) relative with the cell wall (125) of described inclination has nonplanar geometry.
5. support ring as claimed in claim 4 (113) is characterized in that, the cell wall (127) relative with cell wall (125) position of described inclination forms the face along the axial bending of described support ring (113).
6. as the described support ring of one of claim 1 to 5 (113), it is characterized in that the outside (115) of described support ring (113) has coating.
7. combusting room device, have fire tube (101) and mixing chamber (107), wherein, described fire tube (101) has the output (105) that has the support ring (113) that is used for heat shield element (111), and described mixing chamber (107) has the edge that has outstanding buttress (133), and wherein, described buttress (133) is formed for accepting the carrier (109) of described support ring (113), it is characterized in that described support ring (113) is constructed by one of claim 1 to 6 describedly.
8. combusting room device as claimed in claim 7 is characterized in that, the inboard (135) of described buttress (133) and/or the outside (115) of described support ring (113) have coating respectively.
9. combusting room device as claimed in claim 8 is characterized in that, the coating of described buttress (133) is harder than the coating of described support ring (113).
CN2008801132621A 2007-10-26 2008-10-23 Support ring for heat shield elements on aflame tube and a combustion chamber arrangement with said support ring Active CN101855497B (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE102007051649 2007-10-26
DE102007051649.7 2007-10-26
PCT/EP2008/064333 WO2009053417A2 (en) 2007-10-26 2008-10-23 Support ring for heat shield elements on aflame tube and a combustion chamber arrangement with said support ring

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Publication Number Publication Date
CN101855497A true CN101855497A (en) 2010-10-06
CN101855497B CN101855497B (en) 2012-09-05

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CN2008801132621A Active CN101855497B (en) 2007-10-26 2008-10-23 Support ring for heat shield elements on aflame tube and a combustion chamber arrangement with said support ring

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EP (1) EP2201299B1 (en)
CN (1) CN101855497B (en)
AT (1) ATE509236T1 (en)
PL (1) PL2201299T3 (en)
RU (1) RU2478881C2 (en)
WO (1) WO2009053417A2 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104169648A (en) * 2012-03-15 2014-11-26 西门子公司 Heat-shield element for a compressor-air bypass around the combustion chamber

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102017207392A1 (en) 2017-05-03 2018-11-08 Siemens Aktiengesellschaft Silo combustion chamber and method for converting such

Family Cites Families (7)

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Publication number Priority date Publication date Assignee Title
DE8618859U1 (en) * 1986-07-14 1988-01-28 Siemens Ag, 1000 Berlin Und 8000 Muenchen, De
ES2051519T3 (en) * 1990-07-17 1994-06-16 Siemens Ag TUBE PIECE, ESPECIALLY COMBUSTION TUBE WITH REFRIGERATED SUPPORT FRAME FOR A HEAT RESISTANT COATING.
US5749218A (en) * 1993-12-17 1998-05-12 General Electric Co. Wear reduction kit for gas turbine combustors
GB2298267B (en) * 1995-02-23 1999-01-13 Rolls Royce Plc An arrangement of heat resistant tiles for a gas turbine engine combustor
RU2212591C1 (en) * 2002-05-16 2003-09-20 Открытое акционерное общество "Научно-производственное объединение "Сатурн" Gas-turbine engine annular combustion chamber
RU2300706C2 (en) * 2005-05-05 2007-06-10 Открытое акционерное общество "Авиадвигатель" Tubular annular combustion chamber of gas-turbine engine
EP2049840B1 (en) * 2006-08-07 2018-04-11 Ansaldo Energia IP UK Limited Combustion chamber of a combustion installation

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104169648A (en) * 2012-03-15 2014-11-26 西门子公司 Heat-shield element for a compressor-air bypass around the combustion chamber
CN104169648B (en) * 2012-03-15 2016-03-02 西门子公司 Around the heat shield element of the compressed air by-pass collar of combustion chamber

Also Published As

Publication number Publication date
CN101855497B (en) 2012-09-05
RU2010121163A (en) 2011-12-10
ATE509236T1 (en) 2011-05-15
EP2201299A2 (en) 2010-06-30
WO2009053417A3 (en) 2010-05-20
EP2201299B1 (en) 2011-05-11
PL2201299T3 (en) 2011-10-31
RU2478881C2 (en) 2013-04-10
WO2009053417A2 (en) 2009-04-30

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Effective date of registration: 20220209

Address after: Munich, Germany

Patentee after: Siemens energy Global Ltd.

Address before: Munich, Germany

Patentee before: SIEMENS AG