CN204593455U - Hot passage parts integrated combustion chamber - Google Patents
Hot passage parts integrated combustion chamber Download PDFInfo
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- CN204593455U CN204593455U CN201520051793.XU CN201520051793U CN204593455U CN 204593455 U CN204593455 U CN 204593455U CN 201520051793 U CN201520051793 U CN 201520051793U CN 204593455 U CN204593455 U CN 204593455U
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Abstract
The utility model relates to gas turbine art field, specifically disclose a kind of hot passage parts integrated combustion chamber, comprise diffuser, combustion cylinder pressure, water conservancy diversion lining, casing, end cap, nozzle, burner inner liner and changeover portion, it is characterized in that, the outlet of described changeover portion arranges exit guide blade, and described changeover portion is connected with turbine by described exit guide blade.The utility model is without the need to the hermetically-sealed construction between changeover portion and turbine one-level stator blade, simplify the syndeton between combustion turbine transitory section and turbine one-level stator blade and hermetically-sealed construction, decrease vibration, risk that Rig up error causes, effectively increase the life-span, decrease design and processing cost, under the prerequisite ensureing metal temperature safety, can significantly reduce the cold air consumption of changeover portion and turbine junction simultaneously, thus promote gas turbine cycle efficiency.
Description
Technical field
The utility model relates to gas turbine technology field, particularly relates to a kind of gas turbine hot passage parts integrated combustion chamber.
Background technology
The general principle of gas turbine is compressed air by compressor, in a combustion chamber fuel is sprayed in the air after compression and carry out isobaric combustion, then high-temperature high-pressure fuel gas enters turbine and promotes turbine acting, part merit is maintained compressor and is rotated, and a part of merit is then for power or generating in addition.Typically, under the constraint of population parameter and general layout, compressor, combustion chamber, the large parts of turbine three design respectively, are then integrated into whole gas turbine.The parts that in gas turbine, temperature is the highest, for being in combustion chamber second half section and turbine first stage stator blades, are commonly referred to hot passage parts, working medium Thorough combustion in above-mentioned two hot passage parts, and not yet expansion work.
As Figure 1-4, gas-turbine combustion chamber structure of the prior art comprises: diffuser 1, combustion cylinder pressure 2, water conservancy diversion lining 3, casing 4, end cap 5, nozzle 6, burner inner liner 7 and changeover portion 8, the air compressed from compressor is through diffuser 1, enter water conservancy diversion lining 3 adverse current and upwards flow through nozzle 6, burner oil and stream compression air can carry out blending in burner inner liner 7 combustion in nozzle 6, flow through changeover portion 8 afterwards and enter turbine 9 and do work.Usual burner inner liner 7 is circular cylinder; and turbine 9 is annular; therefore multiple changeover portion 8 is needed the multiple circular air stream outlet of burner inner liner 7 to be converted into the fan ring exit be connected with turbine 9; multiple changeover portion 8 is connected with turbine 9 one-level stator blade; there is complicated hermetically-sealed construction 92 and syndeton 91 in junction; generally for the reliability of connection, need multiple connected mode to combine.
For ring-pipe type combustion chamber, the combustion chamber second half section arranges changeover portion, the gas outlet of multiple circular flame cylinder is converted into the annular outlet of multiple fan annular final composition, then is connected with turbine one-level stator blade.Because junction exists multiple changeover portion and turbine one-level stator blade, need a series of connection hermetically-sealed construction, and this place's fuel gas temperature is far away higher than metal allowable temperature, the structure of junction easily goes wrong, and connect the replacing when each maintenance of hermetically-sealed construction needs, in case the damage of one of them connection sealing element causes damage to whole gas turbine.Although above-mentioned design difficulty is considered in existing combustion chamber and turbine design as far as possible, because combustion chamber and turbine two parts separately design, the connectivity problem of combustion chamber and turbine still exists.
In addition, along with the rising of gas turbine parameter, the cooling problem of turbine one-level stator blade leading edge end wall is also on the rise, usual turbine one-level stator blade body is cooled by the design of stator blade internal cooling channel, the cold air that leading edge end wall then depends on outside the changeover portion export amount of combustion chamber cools, this cooling causes extra cold air consumption, and then reduces the efficiency of whole gas turbine.
Utility model content
(1) technical problem that will solve
The purpose of this utility model is to provide a kind of hot passage parts integrated combustion chamber, to simplify syndeton between combustion turbine transitory section and turbine one-level stator blade and hermetically-sealed construction.
(2) technical scheme
In order to solve the problems of the technologies described above, the utility model provides a kind of hot passage parts integrated combustion chamber, comprise diffuser, combustion cylinder pressure, water conservancy diversion lining, casing, end cap, nozzle, burner inner liner and changeover portion, the outlet of described changeover portion arranges exit guide blade, and described changeover portion is connected with turbine by described exit guide blade.
Preferably, described changeover portion and described exit guide blade are integrated.
Preferably, the axis, combustion chamber of described hot passage parts integrated combustion chamber and gas turbine axis are all greater than 0 degree at the angle of axial and circumferential.
Preferably, the axis, combustion chamber of described hot passage parts integrated combustion chamber and the axial angle of gas turbine axis are 15 ° ~ 35 °.
Preferably, the axis, combustion chamber of described hot passage parts integrated combustion chamber and the circumferential angle of gas turbine axis are 10 ° ~ 25 °.
Preferably, the setoff installation angle axis of described exit guide blade and the circumferential angle of gas turbine axis equal the circumferential angle of axis, combustion chamber and gas turbine axis.
Preferably, described exit guide blade is that aerofoil profile is leaf.
Preferably, the downstream of described exit guide blade and the junction of turbine are provided with gaseous film control structure.
Preferably, described gaseous film control structure comprises multiple film cooling holes, and the aperture of described film cooling holes is 1.5mm ~ 3mm, and the gap ratio of described film cooling holes is 3 ~ 6.
(3) beneficial effect
Hot passage parts integrated combustion chamber of the present utility model is without the need to the hermetically-sealed construction between changeover portion and turbine one-level stator blade, simplify the syndeton between combustion turbine transitory section and turbine one-level stator blade and hermetically-sealed construction, decrease vibration, risk that Rig up error causes, effectively increase the life-span, decrease design and processing cost, under the prerequisite ensureing metal temperature safety, can significantly reduce the cold air consumption of changeover portion and turbine junction simultaneously, thus promote gas turbine cycle efficiency; All there is angle its axis, combustion chamber and gas turbine axis in axis and circumferential direction and exports at changeover portion and arrange exit guide blade, and all there is angle axis, combustion chamber and gas turbine axis in axis and circumferential direction, without the need to considering that complex three-dimensional flowing is on cooling impact, simplify turbine one-level stator blade cooling structure design process, simultaneously because existence circumferential angle is installed in combustion chamber, potential realization more short combustor burner inner liner design.
Accompanying drawing explanation
Fig. 1 is the top view of gas-turbine combustion chamber in prior art;
Fig. 2 is the sectional view in the A-A direction of Fig. 1;
Fig. 3 is the enlarged drawing at the B place of Fig. 2;
Fig. 4 is the leaf figure of the turbine one-level stator blade in the C-C direction of Fig. 2;
Fig. 5 is the top view of the hot passage parts integrated combustion chamber of the utility model embodiment;
Fig. 6 is the sectional view in the D-D direction of Fig. 5;
Fig. 7 is the leaf figure of the exit guide blade in the E-E direction of Fig. 6.
In figure, 1: diffuser; 2: combustion cylinder pressure; 3: water conservancy diversion lining; 4: casing; 5: end cap; 6: nozzle; 7: burner inner liner; 8: changeover portion; 9: turbine; 71: axis, combustion chamber; 72: gas turbine axis; 73: exit guide blade established angle axis; 81: exit guide blade; 82: simple aerofoil profile blade profile; 83: existing turbine one-level stator blade blade profile; 91: syndeton; 92: hermetically-sealed construction; 93: turbine one-level stator blade; 94: film cooling holes.
Detailed description of the invention
Below in conjunction with drawings and Examples, embodiment of the present utility model is described in further detail.Following examples for illustration of the utility model, but can not be used for limiting scope of the present utility model.
In description of the present utility model, it should be noted that, term " " center ", " longitudinal direction ", " transverse direction ", " on ", D score, " front ", " afterwards ", " left side ", " right side ", " vertically ", " level ", " top ", " end ", " interior ", orientation or the position relationship of the instruction such as " outward " are based on orientation shown in the drawings or position relationship, only the utility model and simplified characterization for convenience of description, instead of indicate or imply that the device of indication or element must have specific orientation, with specific azimuth configuration and operation, therefore can not be interpreted as restriction of the present utility model.Unless otherwise clearly defined and limited, term " installation ", " being connected ", " connection " should be interpreted broadly, and such as, can be fixedly connected with, also can be removably connect, or connect integratedly; Can be mechanical connection, also can be electrical connection; Can be directly be connected, also indirectly can be connected by intermediary, can be the connection of two element internals.For the ordinary skill in the art, concrete condition the concrete meaning of above-mentioned term in the utility model can be understood.In addition, in description of the present utility model, except as otherwise noted, the implication of " multiple " is two or more.
As illustrated in figs. 5-7, the hot passage parts integrated combustion chamber of the present embodiment comprises: diffuser 1, combustion cylinder pressure 2, water conservancy diversion lining 3, casing 4, end cap 5, nozzle 6, burner inner liner 7 and changeover portion 8; The outlet of changeover portion 8 arranges exit guide blade 81, and changeover portion 8 and exit guide blade 81 are integrated, and therefore, without the need to arranging syndeton or hermetically-sealed construction between changeover portion 8 and exit guide blade 81, changeover portion 8 is connected with turbine 9 by this exit guide blade 81.Typically, connection hermetically-sealed construction in prior art between changeover portion 8 and turbine 9 needs to change when overhauling at every turn, and in the hot passage parts integrated combustion chamber of the present embodiment, without this connection hermetically-sealed construction, then the risk that causes of friction, Rig up error, effectively increases the life-span.
In the present embodiment, axis, combustion chamber 71 and the gas turbine axis 72 of hot passage parts integrated combustion chamber are all greater than 0 degree at the angle of axial and circumferential, namely the layout of changeover portion 8 is except existing except angle at axial direction and gas turbine axis 72, also certain inclination angle is there is in circumferential direction, this angle of inclination, guide effect can be provided for the air-flow leading to turbine 9, the eddy flow that now combustor exit is formed can form the anglec of rotation required for turbine rotor vane, therefore stator blade is reversed without the need to designing turbine one-level, the exit guide blade 81 of simple blade profile is only set in changeover portion 8 outlet.Preferably, axis, combustion chamber 71 is 15 ° ~ 35 ° with the axial angle of gas turbine axis 72, and axis, combustion chamber 71 is 10 ° ~ 25 ° with the circumferential angle of gas turbine axis 72.
As shown in Figure 7, exit guide blade 81 is that simple aerofoil profile is leaf by 82, as shown in Figure 4, turbine one-level stator blade 83 blade profile of the prior art, this internal structure enormously simplify Cooling Design, and cooling capacity also can promote, and can adapt to the gas turbine temperature of more high parameter; The setoff installation angle of exit guide blade 81 is 10 ° ~ 25 °, concrete, setoff installation angle axis 73 and the circumferential angle of gas turbine axis 72 of exit guide blade 81 equal the circumferential angle of axis, combustion chamber 71 and gas turbine axis 72, namely exit guide blade 81 pairs of air-flows only play expansion, but without guide effect, can ensure so not disturb combustion chamber to form eddy flow.
The downstream of exit guide blade 81 and the junction of turbine 9 are provided with gaseous film control structure, namely adopt the end wall of gaseous film control mode to junction to cool; Described gaseous film control structure comprises multiple film cooling holes 94, and the aperture of film cooling holes 94 is 1.5mm ~ 3mm, and the gap ratio of film cooling holes 94 is 3 ~ 6.
The course of work of the hot passage parts integrated combustion chamber of the present embodiment is: the air compressed from compressor is through diffuser 1, enter water conservancy diversion lining 3 adverse current and upwards flow through nozzle 6, in nozzle 6, meeting burner oil and stream compression air carry out blending in burner inner liner 7 combustion, enter changeover portion 8 afterwards, because axis, combustion chamber 71 and gas turbine axis 72 all exist certain angle in axis and circumference, the air-flow in changeover portion 8 exit can produce eddy flow due to wobbler action, this vortex gas-flow is expanded by the carrying out of exit guide blade 81, finally enters turbine 9 and does work.
Hot passage parts integrated combustion chamber of the present utility model is without the need to the hermetically-sealed construction between changeover portion and turbine one-level stator blade, simplify the syndeton between combustion turbine transitory section and turbine one-level stator blade and hermetically-sealed construction, decrease vibration, risk that Rig up error causes, effectively increase the life-span, decrease design and processing cost, under the prerequisite ensureing metal temperature safety, can significantly reduce the cold air consumption of changeover portion and turbine junction simultaneously, thus promote gas turbine cycle efficiency; All there is angle its axis, combustion chamber and gas turbine axis in axis and circumferential direction and exports at changeover portion and arrange exit guide blade, and all there is angle axis, combustion chamber and gas turbine axis in axis and circumferential direction, without the need to considering that complex three-dimensional flowing is on cooling impact, simplify turbine one-level stator blade cooling structure design process, simultaneously because existence circumferential angle is installed in combustion chamber, potential realization more short combustor burner inner liner design.
Embodiment of the present utility model provides for the purpose of example and description, and is not exhaustively or by the utility model be limited to disclosed form.Many modifications and variations are apparent for the ordinary skill in the art.Selecting and describing embodiment is in order to principle of the present utility model and practical application are better described, and enables those of ordinary skill in the art understand the utility model thus design the various embodiments with various amendment being suitable for special-purpose.
Claims (9)
1. a hot passage parts integrated combustion chamber, comprise diffuser, combustion cylinder pressure, water conservancy diversion lining, casing, end cap, nozzle, burner inner liner and changeover portion, it is characterized in that, the outlet of described changeover portion arranges exit guide blade, and described changeover portion is connected with turbine by described exit guide blade.
2. hot passage parts integrated combustion chamber according to claim 1, is characterized in that, described changeover portion and described exit guide blade are integrated.
3. hot passage parts integrated combustion chamber according to claim 2, is characterized in that, the axis, combustion chamber of described hot passage parts integrated combustion chamber and gas turbine axis are all greater than 0 degree at the angle of axial and circumferential.
4. hot passage parts integrated combustion chamber according to claim 3, is characterized in that, the axis, combustion chamber of described hot passage parts integrated combustion chamber and the axial angle of gas turbine axis are 15 ° ~ 35 °.
5. hot passage parts integrated combustion chamber according to claim 4, is characterized in that, the axis, combustion chamber of described hot passage parts integrated combustion chamber and the circumferential angle of gas turbine axis are 10 ° ~ 25 °.
6. hot passage parts integrated combustion chamber according to claim 5, is characterized in that, the setoff installation angle axis of described exit guide blade and the circumferential angle of gas turbine axis equal the circumferential angle of axis, combustion chamber and gas turbine axis.
7. hot passage parts integrated combustion chamber according to claim 2, is characterized in that, described exit guide blade is that aerofoil profile is leaf.
8. hot passage parts integrated combustion chamber according to claim 2, is characterized in that, the downstream of described exit guide blade and the junction of turbine are provided with gaseous film control structure.
9. hot passage parts integrated combustion chamber according to claim 8, is characterized in that, described gaseous film control structure comprises multiple film cooling holes, and the aperture of described film cooling holes is 1.5mm ~ 3mm, and the gap ratio of described film cooling holes is 3 ~ 6.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520051793.XU CN204593455U (en) | 2015-01-23 | 2015-01-23 | Hot passage parts integrated combustion chamber |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520051793.XU CN204593455U (en) | 2015-01-23 | 2015-01-23 | Hot passage parts integrated combustion chamber |
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| CN204593455U true CN204593455U (en) | 2015-08-26 |
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| CN201520051793.XU Active CN204593455U (en) | 2015-01-23 | 2015-01-23 | Hot passage parts integrated combustion chamber |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104595926A (en) * | 2015-01-23 | 2015-05-06 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Integral combustion chamber for heat-channel components |
| CN110234845A (en) * | 2017-01-27 | 2019-09-13 | 通用电气公司 | Integrated flow path configurations |
-
2015
- 2015-01-23 CN CN201520051793.XU patent/CN204593455U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104595926A (en) * | 2015-01-23 | 2015-05-06 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Integral combustion chamber for heat-channel components |
| CN110234845A (en) * | 2017-01-27 | 2019-09-13 | 通用电气公司 | Integrated flow path configurations |
| CN110234845B (en) * | 2017-01-27 | 2022-01-11 | 通用电气公司 | Integrated flow path structure |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right |
Denomination of utility model: Integral combustion chamber for heat-channel components Effective date of registration: 20161104 Granted publication date: 20150826 Pledgee: Tsinghua Holdings Co., Ltd. Pledgor: Beijing Huatsing Gas Turbine & IGCC Technology Co., Ltd. Registration number: 2016990000853 |
|
| PLDC | Enforcement, change and cancellation of contracts on pledge of patent right or utility model | ||
| PC01 | Cancellation of the registration of the contract for pledge of patent right |
Date of cancellation: 20191211 Granted publication date: 20150826 Pledgee: Tsinghua Holdings Co., Ltd. Pledgor: Beijing Huatsing Gas Turbine & IGCC Technology Co., Ltd. Registration number: 2016990000853 |
|
| PC01 | Cancellation of the registration of the contract for pledge of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20191225 Address after: 102209 Beijing Changping District in the future of the national electric investment group Park in the future science city south of Beijing Patentee after: China United heavy-duty gas turbine technology Co., Ltd. Address before: 100084, Beijing, Haidian District science and Technology Park, Tsinghua Science and technology building, block C, 10 Patentee before: Beijing Huatsing Gas Turbine & IGCC Technology Co., Ltd. |
|
| TR01 | Transfer of patent right |