Combustion chambers and burners used to optimize gas turbine ignition and deactivation.

Abstract

This invention relates to the field of energy and power technology, and provides a combustion chamber and burner for optimizing the ignition and shutdown of a gas turbine. The combustion chamber includes a pre-combustion stage structure, a main combustion stage structure, a combustion chamber body, a flow guiding device, and an igniter. The pre-combustion stage structure includes a central body and a pre-combustion stage swirler and a pre-combustion stage outer ring disposed around the central body. The main combustion stage structure is disposed around the pre-combustion stage structure and includes a main combustion stage swirler and a main combustion stage outer ring. The combustion chamber body includes an end wall and a side wall, with the end wall connecting the main combustion stage outer ring and the side wall. The flow guiding device forms a flow guiding channel, with the inlet end of the flow guiding channel connecting to the outlet end of the main combustion stage structure, and the outlet end of the flow guiding channel communicating with the inner cavity of the combustion chamber body. The igniter is disposed on the side wall, and the inner wall of the flow guiding channel is inclined towards the side wall to guide the airflow to the igniter, thereby improving the ignition and shutdown performance of the gas turbine combustion chamber.

Description

Technical Field

[0001] This invention relates to the field of energy and power technology, and in particular to a combustion chamber and burner for optimizing the ignition and de-flame of a gas turbine. Background Technology

[0002] Gas turbines are one of the most important power sources in the energy and power sectors today, widely used in aerospace, aviation, marine, and other industrial fields. While gas turbines have brought immense convenience to humanity, they have also had adverse effects on the global climate. Therefore, low-emission combustion has become one of the key technologies in the research of advanced gas turbine combustors, and lean premixed pre-evaporation combustion technology is currently the most feasible low-emission combustion technology. To meet the requirements of lean premixed combustion in the combustor, the airflow at the combustor head is increased, thereby reducing the equivalence ratio at the combustor head. This will have a serious impact on the combustion stability under low-load operating conditions (flameout), and the problem of lean combustion stability has become a fundamental bottleneck in the development of multi-stage swirl combustion.

[0003] The combustion chamber ignition and shutdown performance determines the engine's stable operating range and is easily affected by environmental factors. When operating under extreme conditions such as high altitude, rain and hail, intake distortion, and transition states, engines often face the possibility of sudden ignition and shutdown. During the ignition and shutdown process in the central staged combustion chamber, the swirling air in the main combustion stage is unlikely to form an ignition nucleus and induce it to propagate towards the flame head, easily leading to the ignition nucleus being blown out or transported downstream to the recirculation zone. The swirling air in the pre-combustion stage entrains some of the main combustion stage air into the flame root, which will cause changes in the flow field and a decrease in the air-fuel ratio in that area, leading to partial or complete ignition shutdown. Summary of the Invention

[0004] This invention aims to at least solve one of the technical problems existing in the prior art. To this end, this invention proposes a combustion chamber for optimizing the ignition and shutdown of a gas turbine, in order to improve the ignition and shutdown performance of the gas turbine combustion chamber.

[0005] The present invention also proposes a burner.

[0006] A combustion chamber for optimizing gas turbine ignition and de-flame according to a first aspect embodiment of the present invention includes:

[0007] A pre-combustion stage structure, the pre-combustion stage structure including a central body and a pre-combustion stage cyclone separator and a pre-combustion stage outer ring disposed around the central body;

[0008] A main combustion stage structure is disposed around the pre-combustion stage structure, and the main combustion stage structure includes a main combustion stage cyclone separator and a main combustion stage outer ring.

[0009] The combustion chamber body includes an end wall and a side wall, wherein the end wall connects the outer ring of the main combustion stage and the side wall;

[0010] A flow guiding device is disposed on the inner surface of the end wall and / or the outlet end face of the outer ring of the main combustion stage, and the flow guiding device forms a flow guiding channel. The inlet end of the flow guiding channel is connected to the outlet end of the main combustion stage structure, and the outlet end of the flow guiding channel is connected to the inner cavity of the combustion chamber body.

[0011] The ignition nozzle is disposed on the side wall, and the inner wall of the flow guiding channel is inclined toward the side wall to guide the airflow toward the ignition nozzle.

[0012] By altering the internal flow field structure of the combustion chamber, the ignition and extinction performance of the combustion chamber can be improved. According to the Conrad effect, a fluid (water or airflow) tends to deviate from its original flow direction and flow along a convex surface. The main combustion stage airflow flows along the inner surface of the guide device, increasing the radial velocity of the main combustion stage. Simultaneously, the ignition nozzle is located on the side wall of the combustion chamber body, and the guide device is angled towards the side wall. This directs the main combustion stage airflow towards the ignition nozzle, making it easier for the air and fuel near the ignition nozzle to be ignited by the electric spark, ultimately improving ignition performance.

[0013] According to one embodiment of the present invention, the pre-combustion stage structure, the main combustion stage structure, the combustion chamber body and the flow guiding device are all coaxially arranged.

[0014] According to one embodiment of the present invention, the flow guiding device has an arc-shaped structure.

[0015] According to one embodiment of the present invention, the flow guiding device is disposed around the main combustion stage structure and is located on the side of the main combustion stage structure adjacent to the ignition nozzle.

[0016] According to one embodiment of the present invention, the inlet and outlet ends of the flow guiding device are both circular in cross-section.

[0017] According to one embodiment of the present invention, the outer ring outlet end face of the pre-combustion stage is coplanar with the outer ring outlet end face of the main combustion stage.

[0018] According to one embodiment of the present invention, the outer ring outlet end face of the main combustion stage and the inner surface of the end wall are coplanar.

[0019] According to one embodiment of the present invention, the distance between the flow guiding device and the inner wall surface of the main combustion stage outer ring is defined as H, the diameter of the annular cavity channel of the main combustion stage outer ring is defined as D, and Ω is defined as H / D, wherein the value range of Ω is: 0≤Ω≤0.3.

[0020] According to one embodiment of the present invention, the distance between the ignition nozzle and the inner side of the combustion chamber main body end wall is defined as L1, the height of the flow guiding device in the direction away from the main combustion stage structure is defined as L2, and δ is defined as L2 / L1, wherein the value range of δ is 0.3≤δ≤0.7.

[0021] According to a second aspect of the present invention, a burner includes a combustion chamber for optimizing gas turbine ignition and de-energization as described in any of the preceding embodiments, wherein the burner is a swirl cup burner, a multi-swirl burner, or a central stage burner.

[0022] The burner according to an embodiment of the present invention, since it includes the above-described combustion chamber, has all the technical effects of the above-described combustion chamber, which will not be repeated here.

[0023] Additional aspects and advantages of the invention will be set forth in part in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention. Attached Figure Description

[0024] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0025] Figure 1 This is a schematic diagram of a partial combustion chamber structure for optimizing gas turbine ignition and de-energization provided in an embodiment of the present invention;

[0026] Figure 2 This is a schematic diagram of the internal streamline of the combustion chamber provided in an embodiment of the present invention;

[0027] Figure 3 This is a partial cross-sectional view of a combustion chamber for optimizing gas turbine ignition and deactivation, provided in an embodiment of the present invention.

[0028] Figure 4 This is a partial cross-sectional view of a combustion chamber for optimizing gas turbine ignition and deactivation, provided in another embodiment of the present invention;

[0029] Figure 5 yes Figure 4 The front view;

[0030] Figure 6 This is a partial cross-sectional view of a combustion chamber for optimizing gas turbine ignition and deactivation, provided in another embodiment of the present invention;

[0031] Figure 7 yes Figure 6 The front view;

[0032] Figure 8 This is a structural diagram of the installation method of the flow guiding device in the right-handed state of the main combustion stage in one embodiment of the present invention;

[0033] Figure 9 yes Figure 8 The front view;

[0034] Figure 10 This is a structural diagram of the installation method of the flow guiding device in the left-hand rotating state of the main combustion stage in one embodiment of the present invention;

[0035] Figure 11 yes Figure 10 The front view;

[0036] Figure 12 This is a schematic diagram of the droplet volume fraction distribution in the combustion chamber of a gas turbine according to an embodiment of the present invention.

[0037] Figure label:

[0038] 1. Central body; 2. Pre-combustion stage outer ring; 3. Main combustion stage outer ring; 4. End wall; 5. Ignition nozzle; 6. Side wall; 7. Pre-combustion stage cyclone separator; 8. Main combustion stage cyclone separator; 11. Flow guiding device; 12. Flow guiding channel. Detailed Implementation

[0039] The embodiments of the present invention will be described in further detail below with reference to the accompanying drawings and examples. The following examples are for illustrative purposes only and should not be construed as limiting the scope of the invention.

[0040] In the description of the embodiments of the present invention, it should be noted that the terms "center," "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing the embodiments of the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on the embodiments of the present invention. In addition, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0041] In the description of the embodiments of the present invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "connected" and "linked" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand the specific meaning of the above terms in the embodiments of the present invention based on the specific circumstances.

[0042] In embodiments of the present invention, unless otherwise explicitly specified and limited, "above" or "below" the second feature can mean that the first feature is in direct contact with the second feature, or that the first feature is in indirect contact with the second feature through an intermediate medium. Furthermore, "above," "on top of," and "over" the second feature can mean that the first feature is directly above or diagonally above the second feature, or simply that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature can mean that the first feature is directly below or diagonally below the second feature, or simply that the first feature is at a lower horizontal level than the second feature.

[0043] In the description of this specification, the references to terms such as "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., refer to specific features, structures, materials, or characteristics described in connection with that embodiment or example, which are included in at least one embodiment or example of the present invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples. Moreover, without contradiction, those skilled in the art can combine and integrate the different embodiments or examples described in this specification, as well as the features of different embodiments or examples.

[0044] Please refer to the reference. Figures 1 to 3 This invention provides a combustion chamber for optimizing gas turbine ignition and de-energization, comprising a pre-combustion stage structure, a main combustion stage structure, a combustion chamber body, a flow guiding device 11, and an igniter 5. The pre-combustion stage structure includes a central body 1 and a pre-combustion stage swirler 7 and a pre-combustion stage outer ring 2 disposed around the central body 1. The main combustion stage structure is disposed around the pre-combustion stage structure and includes a main combustion stage swirler 8 and a main combustion stage outer ring 3. The combustion chamber body includes an end wall 4 and a side wall 6, with the end wall 4 connecting the main combustion stage outer ring 3 and the side wall 6. The flow guiding device 11 is disposed on the inner surface of the end wall 4 and / or the outer ring outlet end face of the main combustion stage outer ring 3, and the flow guiding device 11 forms a flow guiding channel 12. The inlet end of the flow guiding channel 12 is connected to the outlet end of the main combustion stage structure, and the outlet end of the flow guiding channel 12 is connected to the inner cavity of the combustion chamber body. The igniter 5 is disposed on the side wall 6, with the inner wall of the flow guiding channel 12 inclined towards the side wall 6 to guide the airflow to the igniter 5.

[0045] By altering the internal flow field structure of the combustion chamber, the ignition and extinction performance of the combustion chamber is improved. According to the Coanda effect, fluids (water or air) tend to deviate from their original flow direction and flow along a convex surface. The main combustion stage airflow adheres to the inner surface of the guide device 11, increasing the radial velocity of the main combustion stage. Simultaneously, the igniter 5 is located on the side wall 6 of the combustion chamber body, and the guide device 11 is inclined towards the side wall 6. This promotes the flow of the main combustion stage airflow towards the ignition nozzle, making it easier for the air and fuel near the igniter 5 to be ignited by the electric spark, ultimately improving ignition performance.

[0046] Understandably, the flow guiding device 11 is connected to the end wall 4 and / or the outer ring 3 of the main combustion stage through integral machining, welding, or fastener connection. Of course, the connection method between the flow guiding device 11 and the end wall 4 and / or the outer ring 3 of the main combustion stage is not limited to the example given here. The flow guiding device 11 can be in the shape of a ring or a fan-shaped arc, which is not limited here, as long as it can guide the fluid. For example, the flow guiding device can be in the shape of a hollow frustum, that is, in the shape of an outwardly expanding funnel, so that under the entrainment effect of the airflow in the main combustion stage, the air expansion angle of the pre-combustion stage increases, so that the fuel in the pre-combustion stage reaches more near the ignition nozzle 5 through the transport action of the pre-combustion stage structure and the main combustion stage structure, thereby improving the ignition performance.

[0047] like Figure 1 As shown, in one embodiment, α can be defined as the tilt angle of the flow guiding device 11 relative to the inner wall of the outer ring 3 of the main combustion stage. Theoretical analysis and experimental verification show that the range of the α parameter is: 14°≤α<90°, so as to guide the fluid to flow towards the ignition nozzle 5. The specific angle can be adjusted according to the setting position of the ignition nozzle 5. For example, when α is 14°, the tilt angle of the flow guiding device 11 is small, so the ignition nozzle 5 is far away from the flow guiding device 11. When α is 50°, the tilt angle of the flow guiding device 11 is moderate, so the distance between the ignition nozzle 5 and the flow guiding device 11 is moderate. The larger the angle of α, the farther the ignition nozzle 5 is from the flow guiding device 11.

[0048] According to one embodiment of the present invention, the pre-combustion stage structure, the main combustion stage structure, the combustion chamber body and the flow guiding device 11 are all coaxially arranged.

[0049] According to one embodiment of the present invention, the flow guiding device 11 extends along the axial direction of the central body 1. It is worth noting that the flow guiding device 11 can also extend in other directions, as long as a flow guiding channel 12 with its inner wall inclined towards the side wall 6 is formed within the flow guiding device 11. It should be noted that the pre-combustion stage structure, the main combustion stage structure, the combustion chamber body, and the flow guiding device 11 are all coaxially arranged. When air / fuel flows past the vicinity of the inner side wall 6 of the flow guiding device 11, according to the Coanda effect, the air / fuel will deviate from its original flow direction and adhere to the surface of the flow guiding device 11. Thus, the flow guiding device 11 can effectively change the flow state of air / fuel at the outlet of the main pre-combustion stage annular cavity, thereby affecting the spatial distribution of air / fuel throughout the combustion chamber, causing air / fuel to flow towards the ignition nozzle 5, which is beneficial for ignition by the ignition nozzle 5, thereby optimizing the ignition performance of the gas turbine combustion chamber.

[0050] Please refer to the reference. Figure 4 middle Figure 7 According to one embodiment of the present invention, the flow guiding device 11 has an arc-shaped structure.

[0051] In this embodiment, the flow guiding device 11 is arranged in an arc shape to adapt to the outer ring 3 of the main combustion stage, facilitating the guidance of fluid. It is understood that the flow guiding device 11 can be a circular ring structure, a semi-circular arc structure, or a quarter-circular arc structure to save materials when guiding fluid to the ignition nozzle 5. The arc length of the flow guiding device 11 is not limited here.

[0052] According to one embodiment of the present invention, the flow guiding device 11 is arranged around the main combustion stage structure and is located on the side of the main combustion stage structure adjacent to the ignition nozzle 5.

[0053] Please refer to the reference. Figure 5 and Figure 7 For example, if the projected sector-shaped circular angle of the flow guiding device 11 on the end face is defined as β, then the corresponding numerical range is 45°≤β≤360°. Within this circular angle range, the flow guiding device 11 can better improve the ignition and shutdown performance of the gas turbine combustion chamber. When β is 45°, the flow guiding device 11 is located above, and the ignition nozzle 5 is also located above the combustion chamber. In this case, the flow guiding device 11 is positioned adjacent to the ignition nozzle 5 to better guide the fluid to the ignition nozzle 5. When β is 360°, the flow guiding device 11 is annular to guide the fluid in all directions.

[0054] Please refer to the reference. Figures 8 to 11In other embodiments, taking the half-fan-shaped structure of the flow guide device 11 as an example, with the axial vertical plane of the combustion chamber as the reference, the angle between the axial central section of the flow guide device 11 and the axial vertical plane of the combustion chamber is defined as γ. It is stipulated that γ is negative in the counterclockwise direction and positive in the clockwise direction. When air / fuel flows through the main pre-combustion stage swirler 7, it forms a spiral outward expansion trajectory. The main combustion stage swirler 8 and the pre-combustion stage swirler 7 are either left-handed or right-handed. According to the Coanda effect, the installation position of the flow guide device 11 has a certain influence on the air / fuel expansion angle depending on the direction of rotation. Figure 9 This indicates the installation method of the deflector device 11 in the right-hand rotation state of the main combustion stage. The corresponding numerical range is -45°≤γ≤0°, which can be extended to any central angle n (except 360°) corresponding to the projected sector of the deflector device 11. Then the corresponding parameter range is -(n-45°) / 2<γ≤0°. Figure 11 The installation method of the flow guide device 11 in the left-hand rotation state of the main combustion stage indicates that the corresponding numerical range is 0°≤γ≤45°, which can be extended to any central angle n (except 360°) corresponding to the projected sector of the flow guide device 11. Therefore, the corresponding parameter range is 0°≤γ<(n-45°) / 2. Installing the flow guide device 11 according to the above numerical range can better improve the ignition and shutdown performance of the gas turbine combustion chamber.

[0055] The main pre-combustion stage swirl forms two jets, one inside and one outside, within the combustion chamber. Three recirculation zones are formed between these jets: a central recirculation zone, an angular recirculation zone, and a stepped recirculation zone. The angular and central recirculation zones are caused by the expansion of the main pre-combustion stage swirl off its central axis. Due to the larger airflow at the main combustion stage outlet, the air expansion angle of the main combustion stage increases under the action of the guide device 11, causing more air to flow along the combustion chamber sidewall 6. Furthermore, the air velocity difference between the main and pre-combustion stages reduces the internal shear layer pressure between the two jets, forcing the pre-combustion stage air / fuel to flow towards the combustion chamber sidewall 6, reducing the air / fuel layer thickness near the ignition nozzle 5, allowing more fuel to reach the vicinity of the ignition nozzle 5, thereby increasing the probability of successful ignition. Figure 12 As shown, it is understandable that after installing the flow guide device 11, the oil mist angle is larger than that without the flow guide device 11, the height of the central recirculation zone increases, and the oil mist droplets are more likely to reach the vicinity of the ignition nozzle 5, making it easier to ignite successfully.

[0056] like Figure 3 As shown, according to an embodiment of the present invention, the inlet and outlet ends of the flow guiding device 11 are both circular in cross-section.

[0057] In this embodiment, the inlet and outlet ends of the flow guiding device 11 have circular cross-sections to match the circular structure of the main combustion stage. At the same time, this allows the swirling flow generated by the main combustion stage swirler 8 to rotate and flow along the circular structure of the flow guiding device 11, making the fluid flow more stable and optimizing ignition performance.

[0058] like Figure 1 As shown, according to one embodiment of the present invention, the outlet end face of the pre-combustion stage outer ring 2 is coplanar with the outlet end face of the main combustion stage outer ring 3, so that the swirling flow of the pre-combustion stage cyclone separator 7 and the main combustion stage cyclone separator 8 is more stable.

[0059] According to one embodiment of the present invention, the outlet end face of the outer ring 3 of the main combustion stage and the inner surface of the end wall 4 are coplanar. This facilitates the installation of other equipment such as the flow guide device 11 in the combustion chamber.

[0060] According to one embodiment of the present invention, the distance between the flow guiding device 11 and the inner wall surface of the main combustion stage outer ring 3 is defined as H, the diameter of the annular cavity channel of the main combustion stage outer ring 3 is defined as D, and Ω is defined as H / D, with the value range of Ω being 0≤Ω≤0.3.

[0061] According to one embodiment of the present invention, the distance between the ignition nozzle 5 and the inner side of the combustion chamber main body end wall 4 is defined as L1, the height of the flow guiding device 11 in the direction away from the main combustion stage structure is defined as L2, and δ is defined as L2 / L1, with the value range of δ being 0.3≤δ≤0.7.

[0062] According to a second aspect of the present invention, a burner includes a combustion chamber for optimizing gas turbine ignition and de-energization as described in any of the preceding embodiments, wherein the burner is a swirl cup burner, a multi-swirl burner, or a central stage burner.

[0063] The burner according to an embodiment of the present invention, since it includes the above-described combustion chamber, has all the technical effects of the above-described combustion chamber, which will not be repeated here.

[0064] The above embodiments are for illustrative purposes only and are not intended to limit the scope of the invention. Although the invention has been described in detail with reference to the embodiments, those skilled in the art should understand that various combinations, modifications, or equivalent substitutions of the technical solutions of the invention do not depart from the spirit and scope of the invention and should be covered within the scope of the claims of the invention.

Claims

1. A combustion chamber for optimizing the ignition and deactivation of a gas turbine, characterized in that, include: A pre-combustion stage structure, the pre-combustion stage structure including a central body and a pre-combustion stage cyclone separator and a pre-combustion stage outer ring disposed around the central body; A main combustion stage structure is disposed around the pre-combustion stage structure, and the main combustion stage structure includes a main combustion stage cyclone separator and a main combustion stage outer ring. The combustion chamber body includes an end wall and a side wall, wherein the end wall connects the outer ring of the main combustion stage and the side wall; A flow guiding device is disposed on the inner surface of the end wall and / or the outlet end face of the outer ring of the main combustion stage, and the flow guiding device forms a flow guiding channel. The inlet end of the flow guiding channel is connected to the outlet end of the main combustion stage structure, and the outlet end of the flow guiding channel is connected to the inner cavity of the combustion chamber body. The ignition nozzle is disposed on the side wall, and the inner wall of the flow guiding channel is inclined toward the side wall to guide the airflow toward the ignition nozzle; The distance between the flow guiding device and the inner wall of the outer ring of the main combustion stage is defined as H, the diameter of the annular cavity channel of the outer ring of the main combustion stage is defined as D, and Ω is defined as H / D. The value range of Ω is: 0≤Ω≤0.

3. The distance between the ignition nozzle and the inner side of the combustion chamber main body end wall is defined as L1, the height of the flow guiding device in the direction away from the main combustion stage structure is defined as L2, and δ is defined as L2 / L1, with the value range of δ being 0.3≤δ≤0.

7.

2. The combustion chamber for optimizing gas turbine ignition and shutdown according to claim 1, characterized in that, The pre-combustion stage structure, the main combustion stage structure, the combustion chamber body, and the flow guiding device are all coaxially arranged.

3. The combustion chamber for optimizing gas turbine ignition and shutdown according to claim 1, characterized in that, The flow guiding device has an arc-shaped structure.

4. The combustion chamber for optimizing gas turbine ignition and de-flame according to claim 3, characterized in that, The flow guiding device is arranged around the main combustion stage structure and is located on the side of the main combustion stage structure adjacent to the ignition nozzle.

5. The combustion chamber for optimizing gas turbine ignition and shutdown according to claim 1, characterized in that, The inlet and outlet ends of the flow guiding device are both circular in cross-section.

6. The combustion chamber for optimizing gas turbine ignition and shutdown according to claim 5, characterized in that, The outer ring outlet face of the pre-combustion stage is coplanar with the outer ring outlet face of the main combustion stage.

7. The combustion chamber for optimizing gas turbine ignition and shutdown according to claim 6, characterized in that, The outer ring outlet end face of the main combustion stage and the inner surface of the end wall are coplanar.

8. A burner, characterized in that, The burner includes the combustion chamber for optimizing gas turbine ignition and de-flame as described in any one of claims 1-7, wherein the burner is a swirl cup structure burner, a multi-swirl burner, or a central stage burner.

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