CN209782712U - Combustion chamber of gas turbine and gas turbine - Google Patents
Combustion chamber of gas turbine and gas turbine Download PDFInfo
- Publication number
- CN209782712U CN209782712U CN201822028193.8U CN201822028193U CN209782712U CN 209782712 U CN209782712 U CN 209782712U CN 201822028193 U CN201822028193 U CN 201822028193U CN 209782712 U CN209782712 U CN 209782712U
- Authority
- CN
- China
- Prior art keywords
- flame tube
- nozzles
- combustor
- fuel
- gas 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.)
- Active
Links
Abstract
the utility model relates to the field of gas turbines, and discloses a combustion chamber of a gas turbine and a gas turbine, wherein the combustion chamber of the gas turbine comprises a casing and a flame tube arranged in the casing, one end of the flame tube is provided with an end cover, and the other end of the flame tube is provided with a gas outlet; the wall of the flame tube is provided with a plurality of nozzles in the same direction along the circumferential direction, and for each nozzle in the nozzles, the distance between the spraying direction of the nozzle and the center of the circle of the cross section where the nozzle is located is between (0 and r), wherein r is the radius of the flame tube; these nozzles are used to deliver air and fuel into the liner and cause the injected air and fuel to swirl within the liner. In the above embodiment, the plurality of nozzles are circumferentially arranged on the wall of the flame tube, and the air and the fuel ejected from the nozzles form a rotational flow in the flame tube, so that the swirler in the conventional gas turbine combustor is replaced, and the structure of the combustor is simplified.
Description
Technical Field
the utility model relates to a gas turbine field especially relates to a gas turbine's combustion chamber and gas turbine.
Background
The gas turbine is high-end energy equipment for converting chemical energy of fuel into mechanical energy, electric energy and heat energy, has the characteristics of high thermal efficiency, high power density, low pollutant emission and the like, and is widely applied to the fields of distributed energy, cogeneration, airplane tank power and the like.
The gas turbine consists of a gas compressor, a combustion chamber, a turbine and auxiliary machines, wherein combustion reaction of fuel and air occurs in the combustion chamber, and high-temperature gas is generated to push the turbine to do work. The pollutant emissions produced by the combustion process are primarily dependent on the combustion organization within the combustion chamber. In the prior art, a swirler structure is mainly adopted to generate swirl in a flame tube, so that the mixing of air and fuel is enhanced, and stable flame in a backflow area is formed. The swirler is installed in the head of flame tube, comprises structures such as blade, and current low emission combustion chamber adopts the form of a plurality of swirler aggregate erection usually, and the structure is comparatively complicated, has increased the degree of difficulty for design, processing and assembly.
SUMMERY OF THE UTILITY MODEL
the utility model provides a gas turbine's combustion chamber and gas turbine for replace the swirler in traditional gas turbine combustion chamber, simplify the structure of combustion chamber.
The embodiment of the utility model provides a combustion chamber of a gas turbine, which comprises a casing and a flame tube arranged in the casing, wherein one end of the flame tube is provided with an end cover, and the other end of the flame tube is provided with a gas outlet;
A plurality of nozzles are arranged on the wall of the flame tube in the same circumferential direction and can be distributed on the same cross section or different cross sections; for each nozzle in the plurality of nozzles, the distance between the spraying direction of the nozzle and the center of a cross section where the nozzle is located is between (0 and r), wherein r is the radius of the flame tube;
The plurality of nozzles are used for conveying air and fuel into the flame tube and enabling the sprayed air and fuel to form rotational flow in the flame tube.
In the above embodiment, the plurality of nozzles are circumferentially arranged on the wall of the flame tube, and the air and the fuel ejected from the nozzles form a rotational flow in the flame tube, so that the swirler in the conventional gas turbine combustor is replaced, and the structure of the combustor is simplified.
Optionally, the plurality of nozzles are distributed on at least two different cross sections of the flame tube, and at least two nozzles are arranged on each cross section. Along axial direction, the nozzles on different cross sections distribute in the different positions of flame tube section of thick bamboo wall, make the inside reaction zone of flame tube distribute more evenly like this, improved the utilization ratio in flame tube space.
Alternatively, the nozzles on the same cross-section are evenly distributed in the circumferential direction.
Optionally, the projections of the plurality of nozzles on the cross section of the flame tube are not overlapped, that is, the nozzles on different cross sections are arranged in a staggered manner.
Optionally, the end cap is a male end cap, such as a hemispherical end cap or a butterfly end cap.
Specifically, for a group of nozzles closest to the end cover, the ratio H/D between the height H of the cross section of the nozzle from the top of the end cover and the diameter D of the flame tube is not more than 1.5. When H is too large, some non-reaction areas are formed at the head of the flame tube, and head space is wasted.
Optionally, the nozzle comprises an inner sleeve and an outer sleeve sleeved on the inner sleeve, and the inner sleeve is communicated with the gas pipeline and used for conveying fuel into the flame tube; the outer sleeve is communicated with an air channel between the casing and the flame tube and is used for conveying air into the flame tube.
Specifically, the inner sleeve and the outer sleeve are coaxially arranged.
Specifically, one end of the inner sleeve facing the flame tube is located in the outer sleeve or flush with the outer sleeve. When the head of the inner sleeve is positioned in the outer sleeve, the fuel is sprayed out of the inner sleeve and then premixed with air, and then enters the flame tube; when the head of the inner sleeve is flush with the head of the outer sleeve, the gas and the air are diffused and combusted in the flame tube.
specifically, one end, close to the gas outlet, of the cylinder wall of the flame tube is further provided with a plurality of mixing holes, and the plurality of mixing holes are communicated with the air channel. Fresh air enters the flame tube through the mixing holes to reduce the temperature of the fuel gas emitted from the fuel gas outlet.
The embodiment of the utility model provides a gas turbine is still provided, include above-mentioned arbitrary combustion chamber. In the combustion chamber, the plurality of nozzles are arranged on the wall of the flame tube along the circumferential direction, so that the sprayed air and fuel form rotational flow in the flame tube, a swirler in the traditional gas turbine combustion chamber is replaced, the structure of the combustion chamber is simplified, and the installation is facilitated.
Drawings
FIG. 1 is a front view of a flame tube according to an embodiment of the present invention;
FIG. 2 is a side view of the liner shown in FIG. 1;
Fig. 3 is a bottom view of the liner shown in fig. 1.
Reference numerals:
10-flame tube 11-fuel outlet
20-nozzle 30-end cap 40-mixing hole
Detailed Description
in order to make the objects, technical solutions and advantages of the present invention clearer, the present invention will be described in further detail with reference to the accompanying drawings, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.
The embodiment of the utility model provides a combustion chamber of a gas turbine, which comprises a casing and a flame tube arranged in the casing, wherein one end of the flame tube is provided with an end cover, and the other end is provided with a gas outlet;
a plurality of nozzles are arranged on the wall of the flame tube in the same circumferential direction and can be distributed on the same cross section or different cross sections; for each nozzle in the nozzles, the distance between the injection direction of the nozzle and the center of the cross section where the nozzle is located is between (0 and r), wherein r is the radius of the flame tube;
These nozzles are used to deliver air and fuel into the liner and cause the injected air and fuel to swirl within the liner.
In the above embodiment, the plurality of nozzles are circumferentially arranged on the wall of the flame tube, and the air and the fuel sprayed from the nozzles can form a rotational flow in the flame tube, so as to enhance the mixing of the air and the fuel, reduce the emission of pollutants such as nitrogen oxides and carbon monoxide, and replace a swirler in a conventional gas turbine combustion chamber, thereby simplifying the structure of the combustion chamber.
For a clearer understanding of the specific structure of the combustion chamber provided by the embodiments of the present invention, reference will now be made to the following detailed description taken in conjunction with the accompanying drawings.
The combustion chamber comprises a casing and a flame tube 10 arranged in the casing, wherein the structure of the flame tube 10 is shown in fig. 1-3, wherein fig. 1 is a front view of the flame tube 10, fig. 2 is a side view of the flame tube 10, and fig. 3 is a bottom view of the flame tube 10. Referring to fig. 1 and 2, one end of the flame tube 10 is provided with an end cover 30, the other end is provided with a gas outlet 11, and the wall of the flame tube 10 is provided with a plurality of nozzles 20 along the same circumferential direction, and the nozzles 20 may be formed in a row and distributed on the same cross section of the flame tube 10, or may also be formed in two or more rows and distributed on different cross sections of the flame tube 10; for each nozzle 20 of the nozzles 20, the distance between the injection direction of the nozzle 20 and the center of the cross section of the nozzle 20 is between (0, r), where r is the radius of the flame tube 10, that is, the nozzles 20 are obliquely arranged along the wall of the flame tube 10, and the included angle α between the injection direction of each nozzle 20 and the radial direction of the nozzle 20 is between 0 ° and 90 °; the nozzles 20 may be arranged in a clockwise or counterclockwise direction to deliver air and fuel into the liner 10 and swirl the injected air and fuel within the liner 10. Functionally, the arrangement of the nozzles 20 enhances the mixing of air and fuel, so that the combustion reaction of the fuel in the flame tube 10 is more complete, which is beneficial to reducing the emission of pollutants such as nitrogen oxides and carbon monoxide in the combustion process, and the combustion classification can be realized by opening or closing part of the nozzles 20, which is beneficial to maintaining efficient and stable combustion of the combustion chamber during variable load operation; structurally, these nozzles 20 replace the swirler in a conventional gas turbine combustor, which simplifies the structure of the combustor and facilitates design and installation.
In the prior art, the low-emission combustor generally adopts a multi-stage swirler structure, and a plurality of swirlers are combined and installed at the head of the flame tube 10, in use, the swirlers can generate a large backflow area in the flame tube 10, which helps to stabilize the flame, but also causes a waste of space in the flame tube 10, and is difficult to form a very uniform mixing and reaction distribution in the flame tube 10, resulting in a local over-high or under-low temperature. In this embodiment, a plurality of rows of nozzles 20 may be axially disposed on the wall of the flame tube 10, each row of nozzles 20 is circumferentially distributed and located on one cross section of the flame tube 10, such that a group of nozzles 20 on each cross section is equivalent to a swirler and is distributed at different positions of the wall of the flame tube 10 in the axial direction, so that the distribution of the reaction zone in the flame tube 10 is more uniform, the utilization rate of the space of the flame tube 10 is improved, and simultaneously, in the using process, the air and the fuel sprayed from the nozzles 20 on different cross sections jointly form a swirl flow in the flame tube 10, thereby reducing the component velocity of the airflow in the axial direction, improving the retention time of the airflow in the flame tube 10, making the mixing and combustion reaction of the fuel in the flame tube 10 more sufficient, and effectively reducing the emission of pollutants such as nitrogen oxides and carbon monoxide.
In a specific embodiment, the nozzles 20 are distributed on at least two different cross sections of the combustor basket 10, and each cross section has at least two nozzles 20, so that the air and fuel ejected from a group of nozzles 20 on each cross section can form a swirl flow in the combustor basket 10, specifically, a group of nozzles 20 on the same cross section are uniformly distributed along the circumferential direction, or other distribution modes such as random distribution can also be adopted; in addition, in order to make the combination effect of the nozzles 20 on different cross sections better, the projections of the nozzles 20 on a certain cross section of the flame tube 10 do not coincide with each other, that is, the nozzles 20 on different cross sections are arranged in a staggered manner, and more specifically, the projections of the nozzles 20 on a certain cross section of the flame tube 10 are uniformly distributed along the circumferential direction, which is beneficial to generating stable rotational flow in the flame tube 10. It should be noted that the above is only a part of the embodiments, and besides the above arrangement, other similar arrangement manners may be adopted on the wall of the flame tube 10, and detailed description thereof is omitted.
Referring to fig. 1 to 3 together, four nozzles 20 are arranged on the wall of the flame tube 10, and arranged in two rows on two different cross sections, two nozzles 20 are arranged on each cross section and uniformly distributed along the circumference, wherein the connecting line of two nozzles 20 on one cross section is perpendicular to the connecting line of two nozzles 20 on the other cross section. In the combustion chamber, the number of rows of the nozzles 20 arranged on the flame tube 10 and the number of each row of the nozzles 20 are related to the diameter of the flame tube 10, the mixing effect of air and fuel in the flame tube 10 can be best through certain combination, the non-reaction area is minimum, and the utilization rate of the space of the flame tube 10 is effectively improved.
In the combustion chamber, the nozzle 20 is used for delivering air and fuel into the flame tube 10, and when the structure of the nozzle 20 is specifically provided, in this embodiment, the nozzle 20 includes an inner sleeve and an outer sleeve sleeved on the inner sleeve, the inner sleeve and the outer sleeve are both communicated with the flame tube 10, the inner sleeve is also communicated with a gas pipeline and is used for delivering fuel into the flame tube 10, the outer sleeve is also communicated with an air passage between the casing and the flame tube 10 and is used for delivering air into the flame tube 10, wherein an air inlet is formed in the casing, and high-pressure air enters the air passage between the casing and the flame tube 10 through the air inlet. The inner sleeve and the outer sleeve are combined to realize the transmission of fuel and air, the structure is simple, the installation is convenient, concretely, one end of the inner sleeve facing the flame tube 10 is positioned in the outer sleeve or is flush with the outer sleeve, one end of the inner sleeve facing the flame tube 10 is a fuel outlet, when the outlet is positioned in the outer sleeve, the fuel is sprayed out from the inner sleeve and then premixed with the air, and then enters the flame tube 10; when the outlet is flush with the outer sleeve, the gas and air are combusted while being diffused inside the liner 10. More specifically, the inner sleeve and the outer sleeve are coaxially arranged, the central passage is a fuel circulation passage, and the outer annular passage is an air circulation passage.
In the combustion chamber, as shown in fig. 1 and 2, an end cover 30 forms a plug at one end of a flame tube 10, nozzles 20 arranged on the wall of the flame tube 10 provide air and fuel for the flame tube 10, specifically, the end cover 30 is a convex end cover 30, such as a hemispherical end cover 30 or a butterfly end cover 30, and the like, one end of the flame tube 10 close to the end cover 30 may be provided with one or more groups of nozzles 20 along the wall, each group of nozzles 20 is circumferentially distributed, for one group of nozzles 20 closest to the end cover 30, the ratio H/D between the height H from the cross section where the nozzles 20 are located to the top of the end cover 30 and the diameter D of the flame tube 10 is not greater than 1.5, and when H is too large, the head of the flame tube 10 will form some non-reaction regions, resulting in waste of. In addition, a plurality of mixing holes 40 are further formed at one end of the cylinder wall of the combustor basket 10 close to the gas outlet 11, the mixing holes 40 are communicated with an air passage between the casing and the combustor basket 10 and are arranged in one row or two rows for supplementing fresh air into the combustor basket 10 and reducing the temperature of the gas at the fuel outlet position, and the fuel outlet is convergent, if the diameter of the outlet is too large, the central part of the outlet will generate backflow, which causes the gas turbine to fail to work normally.
As can be seen from the above description, in the embodiment of the present invention, by disposing a plurality of nozzles 20 along the circumferential direction on the wall of the flame tube 10, and making the air and fuel ejected from these nozzles 20 form a rotational flow in the flame tube 10, a swirler in a conventional gas turbine combustor is replaced, the structure of the combustor is simplified, and the installation is facilitated.
The embodiment of the utility model also provides a gas turbine, including any one above-mentioned combustion chamber; besides the combustion chamber, the gas turbine also comprises a compressor, a turbine and other components, wherein a combustion reaction of fuel and air occurs in the combustion chamber, a plurality of nozzles 20 are circumferentially arranged on the wall of the flame tube 10, the nozzles 20 can be distributed on the same cross section or different cross sections, and the nozzles 20 are used for conveying air and fuel into the flame tube 10, so that the jetted air and fuel form a rotational flow in the flame tube 10, the mixing of the air and the fuel is enhanced, the reaction is more sufficient, the gas generated by the combustion reaction is jetted out from a fuel outlet on the flame tube 10, and the turbine is pushed to do work, so that chemical energy is converted into mechanical energy.
it will be apparent to those skilled in the art that various changes and modifications may be made without departing from the spirit and scope of the invention. Thus, if such modifications and variations of the present invention fall within the scope of the claims and their equivalents, the present invention is also intended to include such modifications and variations.
Claims (9)
1. The combustion chamber of the gas turbine is characterized by comprising a casing and a flame tube arranged in the casing, wherein one end of the flame tube is provided with an end cover, and the other end of the flame tube is provided with a gas outlet;
The wall of the flame tube is provided with a plurality of nozzles in the same direction along the circumferential direction, and for each nozzle in the plurality of nozzles, the distance between the spraying direction of the nozzle and the circle center of the cross section where the nozzle is located is larger than zero and smaller than the radius of the flame tube;
The plurality of nozzles are used for conveying air and fuel into the flame tube and enabling the sprayed air and fuel to form rotational flow in the flame tube;
The plurality of nozzles are distributed on at least two different cross sections of the flame tube, and each cross section is provided with at least two nozzles.
2. The combustor of claim 1, wherein a plurality of nozzles located on the same cross-section are evenly distributed in a circumferential direction.
3. The combustor of claim 1, wherein the projections of said plurality of nozzles onto said liner cross-section do not coincide with each other.
4. The combustor of claim 1, wherein said end cap is a male end cap.
5. The combustor of claim 1, wherein for a group of nozzles closest to the end cover, a ratio H/D between a height H of a cross-section of the nozzles to a top of the end cover and a diameter D of the liner is no greater than 1.5.
6. the combustor of claim 1, wherein said nozzle includes an inner sleeve and an outer sleeve mounted over said inner sleeve, said inner sleeve communicating with a gas line for delivering fuel into said flame tube; the outer sleeve is communicated with an air channel between the casing and the flame tube and is used for conveying air into the flame tube.
7. the combustor of claim 6, wherein an end of said inner sleeve facing said liner is located within or flush with said outer sleeve.
8. The combustor of claim 6, wherein the end of the cylindrical wall of the liner near the gas outlet is further provided with a plurality of mixing holes, and the plurality of mixing holes are communicated with the air channel.
9. A gas turbine comprising the combustor according to any one of claims 1 to 8.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822028193.8U CN209782712U (en) | 2018-12-04 | 2018-12-04 | Combustion chamber of gas turbine and gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822028193.8U CN209782712U (en) | 2018-12-04 | 2018-12-04 | Combustion chamber of gas turbine and gas turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN209782712U true CN209782712U (en) | 2019-12-13 |
Family
ID=68787845
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201822028193.8U Active CN209782712U (en) | 2018-12-04 | 2018-12-04 | Combustion chamber of gas turbine and gas turbine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN209782712U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109404965A (en) * | 2018-12-04 | 2019-03-01 | 新奥能源动力科技（上海）有限公司 | A kind of combustion chamber of gas turbine and gas turbine |
-
2018
- 2018-12-04 CN CN201822028193.8U patent/CN209782712U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109404965A (en) * | 2018-12-04 | 2019-03-01 | 新奥能源动力科技（上海）有限公司 | A kind of combustion chamber of gas turbine and gas turbine |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US9599343B2 (en) | Fuel nozzle for use in a turbine engine and method of assembly | |
| JP6196868B2 (en) | Fuel nozzle and its assembly method | |
| US20120180487A1 (en) | System for flow control in multi-tube fuel nozzle | |
| CN110056906B (en) | Coaxial staged swirl and blending integrated head for gaseous fuel combustor | |
| CN111396927B (en) | Two-dimensional array low-pollution combustion device without traditional swirler | |
| CN107575864B (en) | Linear low-nitrogen gas combustion head | |
| CN114294680A (en) | Micro-premix combustion chamber of center-staged gas turbine | |
| CN106524225B (en) | The three vortex system tissue burned flame cylinders suitable for advanced low pollution turbogenerator | |
| CN112361335B (en) | Combustor based on multizone burning | |
| CN104373962A (en) | Blade type air inlet swirl nozzle for combustion chamber of gas turbine | |
| CN111928295A (en) | Micro-premixing on-duty nozzle assembly and micro-premixing combustion chamber of gas turbine | |
| US9677766B2 (en) | Fuel nozzle for use in a turbine engine and method of assembly | |
| CN216346263U (en) | Novel marsh gas low-nitrogen burner | |
| CN113503565B (en) | Contraction and expansion type annular evaporation pipe for micro turbine engine | |
| CN209782712U (en) | Combustion chamber of gas turbine and gas turbine | |
| CN112555829B (en) | Spray gun capable of generating supersonic airflow | |
| CN109140500A (en) | A kind of nozzle of combustion chamber, combustion chamber and miniature gas turbine | |
| CN204313313U (en) | Gas-turbine combustion chamber nozzle | |
| CN216143778U (en) | Combustor and premixed air inlet type backflow annular combustion chamber | |
| CN115143459A (en) | Injection premixing smoke internal circulation low-nitrogen combustor | |
| CN215892445U (en) | Fuel nozzle for realizing premixed combustion and diffusion combustion | |
| CN212408659U (en) | Infrared burner | |
| CN114811582A (en) | Double-swirl low-nitrogen combustor | |
| CN204388126U (en) | A kind of gas-turbine combustion chamber blade Inlet Swirl nozzle | |
| CN109611889B (en) | Gas fuel nozzle assembly |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |