CN113606607B

CN113606607B - Nozzle, and combustion chamber and gas turbine having the same

Info

Publication number: CN113606607B
Application number: CN202110961482.7A
Authority: CN
Inventors: 邓爱明; 郭庆波; 赵光军; 耿杰峰; 吕煊
Original assignee: China United Heavy Gas Turbine Technology Co Ltd
Current assignee: China United Heavy Gas Turbine Technology Co Ltd
Priority date: 2021-08-20
Filing date: 2021-08-20
Publication date: 2023-05-16
Anticipated expiration: 2041-08-20
Also published as: CN113606607A

Abstract

The invention relates to a nozzle, a combustion chamber and a gas turbine with the nozzle. The central body is provided with an on-duty fuel channel and a premixed fuel channel, the sleeve is sleeved on the central body, an annular oxygen-containing gas channel is formed between the sleeve and the central body, the cyclone comprises blades, the blades are rotatably arranged in the oxygen-containing gas channel, the rotation axes of the blades are parallel to the extending direction of the oxygen-containing gas channel, the blades are provided with the fuel channel, and the premixed fuel channel is communicated with the oxygen-containing gas channel through the fuel channel. The blades of the cyclone of the nozzle can rotate, can improve the uniformity of mixing oxygen-containing gas and fuel, and can be suitable for different types of fuel.

Description

Nozzle, and combustion chamber and gas turbine having the same

Technical Field

The invention relates to the technical field of power device combustion, in particular to a nozzle, a combustion chamber with the nozzle and a gas turbine.

Background

In the related art, a nozzle of a gas turbine mixes air and fuel by using a swirler, and improving mixing uniformity is beneficial to reducing hot spot temperature and pollution emission. However, the swirler of the related art nozzle is fixed, and the air and the fuel are unevenly mixed when the gas turbine is operated at a low load. Moreover, the blades of the swirler are fixed, and the swirler can only aim at specific fuel, so that the applicability is poor.

Disclosure of Invention

The present invention has been made based on the findings and knowledge of the inventors regarding the following facts and problems:

heavy duty gas turbine combustors have been developed to meet low pollutant emissions requirements primarily through premixed combustion technology. The homogeneous blend technology is the core technology of heavy duty gas turbine combustor nozzles. The more uniform the airflow blend, the lower the maximum temperature of combustion, the lower the hot spot temperature, and the more uniform the outlet temperature distribution, thereby reducing the difficulty in turbine structure and cooling design. However, at low part load, reduced fuel flow results in reduced fuel pressure, reduced penetration depth of the fuel jet, reduced uniformity of fuel and air mixing in the circumferential direction, and increased pollutant emissions and hot spot temperatures. Furthermore, current solutions generally address specific gaseous fuels, and as the type of gaseous fuel changes, density and heating value changes will result in mass flow changes that affect injection pressure, the nozzle configuration will require adaptation.

The present invention aims to solve at least one of the technical problems in the related art to some extent.

To this end, embodiments of the present invention provide a nozzle whose swirler vanes are rotatable, which can improve the uniformity of mixing of oxygen-containing gas and fuel, and which can also be adapted to different kinds of fuel.

Embodiments of the present invention provide a combustion chamber that can improve the uniformity of mixing of oxygen-containing gas and fuel, and can also be applied to different kinds of fuel.

Embodiments of the present invention provide a gas turbine that can improve the uniformity of mixing of oxygen-containing gas and fuel, and can also be adapted to different types of fuel.

A nozzle according to an embodiment of the present invention includes:

the central body is provided with an on-duty fuel channel and a premix fuel channel;

the sleeve cover is sleeved on the central body, and an annular oxygen-containing gas channel is formed between the sleeve cover and the central body; and

the cyclone comprises blades, the blades are rotatably arranged in the oxygen-containing gas channel, the rotation axes of the blades are parallel to the extending direction of the oxygen-containing gas channel, the blades are provided with fuel channels, and the premixed fuel channels are communicated with the oxygen-containing gas channel through the fuel channels.

According to the nozzle provided by the embodiment of the invention, the blades can rotate, the blades are provided with the fuel channels communicated with the premixed fuel channel and the oxygen-containing gas channel, and the blades can rotate under the action of the air flow of the oxygen-containing gas, so that the mixing uniformity degree of the oxygen-containing gas and the fuel can be improved, and different types of fuels and the oxygen-containing gas can be uniformly mixed.

Therefore, the nozzle provided by the embodiment of the invention can improve the uniformity of mixing of oxygen-containing gas and fuel, and can be applied to different types of fuels.

In some embodiments, the central body comprises:

a center tube having the duty fuel passage; and

and the outer tube is sleeved on the central tube, and the premixed fuel channel is defined between the outer tube and the central tube.

In some embodiments, a portion of the outer tube is rotatably disposed, the axis of rotation of the outer tube being parallel to the direction of extension of the oxygen-containing gas channel, the portion of the outer tube being connected to the blades for rotation of the blades.

In some embodiments, the outer tube comprises a first tube section, the portion and a second tube section, the first tube section and the center tube defining the premix fuel passage therebetween, the swirler further comprises a hub, the portion of the outer tube forms the hub, the first tube section, the hub and the second tube section are sequentially connected in an extending direction of a rotational axis of the vane, a central axis of the hub, a central axis of the first tube section and a central axis of the second tube section coincide with each other, wherein the hub has a fuel inlet in communication with the premix fuel passage, the vane is provided on the hub, and the fuel inlet and the fuel passage are in communication.

In some embodiments, the hub and the blade are integrally formed.

In some embodiments, the nozzle further comprises a bearing, an inner ring of the bearing is sleeved on the central tube, and the hub is sleeved on an outer ring of the bearing.

In some embodiments, the central tube comprises a third tube section, a corrugated tube section and a fourth tube section which are connected in sequence, and the inner ring of the bearing is sleeved on at least one of the third tube section, the corrugated tube section and the fourth tube section.

In some embodiments, the vanes and the shroud are spaced apart in a radial direction of the oxygen-containing gas channel.

The combustion chamber according to an embodiment of the present invention comprises the nozzle according to any of the embodiments described above.

A gas turbine according to an embodiment of the invention comprises a combustion chamber according to any of the embodiments described above.

Drawings

Fig. 1 is a schematic view showing the structure of a nozzle according to an exemplary embodiment of the present invention.

Fig. 2 is a schematic structural view of a central tube according to an exemplary embodiment of the present invention.

Fig. 3 is a schematic view showing the structure of the outer tube and the cyclone according to an exemplary embodiment of the present invention.

Fig. 4 is a schematic view of a cyclone according to an exemplary embodiment of the present invention.

Reference numerals:

a nozzle 10;

a central body 100; a central tube 110; a third pipe section 111; corrugated tube segment 112; a fourth pipe section 113; an outer tube 120; a first pipe section 121; a second tube segment 122;

a shroud 200;

a cyclone 300; a blade 310; a fuel passage 311; a fuel outlet 312; a hub 320; a fuel inlet 321;

a bearing 400;

an on duty fuel channel 510; premix fuel passage 520; an oxygen-containing gas channel 530.

Detailed Description

Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings. The embodiments described below by referring to the drawings are illustrative and intended to explain the present invention and should not be construed as limiting the invention.

A nozzle 10 according to an embodiment of the present invention is described below with reference to the accompanying drawings.

As shown in fig. 1 to 4, a nozzle 10 according to an embodiment of the present invention includes a center body 100, a shroud 200, and a swirler 300.

The center body 100 has a duty fuel passage 510 and a premix fuel passage 520, and the shroud 200 is fitted over the center body 100, with an annular oxygen-containing gas passage 530 formed between the shroud 200 and the center body 100.

The swirler 300 includes the vanes 310, the vanes 310 being rotatably provided in the oxygen-containing gas channel 530, the rotational axis of the vanes 310 being parallel to the extending direction (left-right direction in fig. 1) of the oxygen-containing gas channel 530. The vane 310 has a fuel passage 311, and a premix fuel passage 520 communicates with an oxygen-containing gas passage 530 through the fuel passage 311.

The blades 310 and the shroud 200 are spaced apart in the radial direction of the oxygen-containing gas channel 530, so that the blades 310 can rotate about their rotational axes.

It will be appreciated that there is at least one blade 310.

According to the nozzle 10 of the embodiment of the present invention, the vane 310 is rotatable, and the vane 310 has the fuel passage 311 communicating the premix fuel passage 520 and the oxygen-containing gas passage 530, and the fuel in the premix fuel passage 520 can enter the oxygen-containing gas passage 530 through the fuel passage 311, so that the fuel can be mixed with the oxygen-containing gas in the oxygen-containing gas passage 530.

The vane 310 can rotate under the action of the air flow of the oxygen-containing gas, and the fuel in the fuel channel 311 has axial and radial speeds, so that the oxygen-containing gas and the fuel are uniformly mixed, and the mixing degree of the oxygen-containing gas and the fuel can be improved.

In addition, the fuel passages 311 are provided in the vane 310, and the fuel and the oxygen-containing gas can be uniformly mixed when the vane 310 rotates, regardless of the kind of fuel, so the nozzle 10 of the embodiment of the present invention can uniformly mix different kinds of fuel and the oxygen-containing gas.

Thus, the nozzle 10 according to the embodiment of the present invention can improve the uniformity of mixing of the oxygen-containing gas and the fuel, thereby reducing the hot spot temperature, and can be applied to different types of fuels.

In some embodiments, as shown in fig. 1-3, the center body 100 includes a center tube 110 and an outer tube 120, the center tube 110 having an on-duty fuel passage 510, the outer tube 120 being sleeved over the center tube 110, the outer tube 120 and the center tube 110 defining a premix fuel passage 520 therebetween.

Specifically, the outer tube 120 is sleeved on the central tube 110, the outer peripheral surface of the central tube 110 and the inner peripheral surface of the outer tube 120 are spaced apart in the radial direction of the central tube 110, the lumen of the central tube 110 forms a duty fuel channel 510, and the annular cavity defined by the outer peripheral surface of the central tube 110 and the inner peripheral surface of the outer tube 120 forms a premix fuel channel 520.

Thus, the on-duty fuel passage 510 and the premix fuel passage 520 are not in communication, and the fuel in the premix fuel passage 520 and the fuel in the on-duty fuel passage 510 are not mixed, and the fuel in the premix fuel passage 520 can enter the oxygen-containing gas passage 530 through the fuel passage 311.

It will be appreciated that the fuel within the premix fuel passage 520 mixes with the oxygen-containing gas within the oxygen-containing gas passage 530 to form a combustible mixture and flows to the right, which forms a stable ignition source at the right end of the shroud 200, thereby enabling a reduction in hot spot temperatures and pollutant emission concentrations.

In some embodiments, a portion of the outer tube 120 is rotatably disposed, the rotational axis of the outer tube 120 being parallel to the direction of extension of the oxygen-containing gas channel 530, the portion of the outer tube 120 being connected to the blades 310 for rotation of the blades 310.

As shown in fig. 1, the portion of the outer tube 120 can rotate, the rotational axis of the portion of the outer tube 120 coincides with the rotational axis of the vane 310, and the portion of the outer tube 120 is connected to the vane 310, so that the portion of the outer tube 120 and the vane 310 can rotate together, thereby facilitating the communication of the fuel passage 311 with the premix fuel passage 520.

In some embodiments, as shown in fig. 1 and 3, the outer tube 120 includes a first tube segment 121, the portion, and a second tube segment 122, with a premix fuel passage 520 defined between the first tube segment 121 and the base pipe 110. That is, the premix fuel passage 520 is formed between the inner peripheral surface of the first pipe section 121 and the outer peripheral surface of the center pipe 110.

The swirler 300 further comprises a hub 320, the portion of the outer tube 120 forming the hub 320, the first tube section 121, the hub 320 and the second tube section 122 being connected in sequence in the direction of extension of the rotational axis of the vane 310, and the hub 320 being rotatable relative to the first tube section 121 and the second tube section 122, the central axis of the hub 320, the central axis of the first tube section 121 and the central axis of the second tube section 122 coinciding with each other. That is, the first pipe segment 121, the hub 320 and the second pipe segment 122 are connected in sequence in the left-right direction, i.e., the first pipe segment 121 is located at the left side, the second pipe segment 122 is located at the right side, the hub 320 is connected between the first pipe segment 121 and the second pipe segment 122,

as shown in fig. 4, the hub 320 has fuel inlet holes 321 communicating with the premix fuel passage 520, and the vanes 310 are provided on the hub 320, and the fuel inlet holes 321 communicate with the fuel passage 311. It will be appreciated that hub 320 has an interior cavity and that the interior cavity of hub 320 communicates with premix fuel passage 520 and that fuel inlet 321 communicates with premix fuel passage 520 through the interior cavity of hub 320.

That is, the vane 310 can rotate together with the hub 320, and the fuel passage 311 communicates with the premix fuel passage 520 through the fuel inlet 321, and the fuel in the premix fuel passage 520 can enter the oxygen-containing gas passage 530.

As shown in fig. 4, the vane 310 has the fuel outlet holes 312, and the fuel outlet holes 312 communicate with the oxygen-containing gas channel 530 and the fuel channel 311, so that the fuel in the premixed fuel channel 520 enters the fuel channel 311 through the fuel inlet holes 321 and is further connected to the oxygen-containing gas channel 530 through the fuel outlet holes 312.

It will be appreciated that the plurality of fuel outlet holes 312, and the vanes 310 rotate as fuel is discharged from the fuel outlet holes 312, the fuel has a radial velocity, and the fuel can be uniformly injected in the circumferential direction of the shroud 200, so that the fuel and the oxygen-containing gas are uniformly mixed, and the fuel can also move rightward under the driving of the air flow of the oxygen-containing gas.

Preferably, the hub 320 and the blades 310 are integrally formed.

In some embodiments, as shown in fig. 1, the nozzle 10 of the embodiment of the present invention further includes a bearing 400, wherein an inner ring of the bearing 400 is sleeved on the central tube 110, and a hub 320 is sleeved on an outer ring of the bearing 400. Accordingly, the bearing 400 supports the hub 320 such that the hub 320 can rotate.

As shown in fig. 1 and 2, the center tube 110 includes a third tube section 111, a bellows section 112, and a fourth tube section 113 connected in sequence, and an inner race of the bearing 400 is sleeved on at least one of the third tube section 111, the bellows section 112, and the fourth tube section 113.

The deformation of the central tube 110 is easily generated after the temperature change, that is, the bellows segment 112 stretches in the left-right direction, and the deformation of the central tube 110 can be compensated.

It will be appreciated that the first tube segment 121 corresponds to the third tube segment 111, the hub 320 corresponds to the bellows segment 112, and the second tube segment 122 corresponds to the fourth tube segment 113. That is, the third pipe section 111 is located on the left side, the fourth pipe section 113 is located on the right side, and the bellows section 112 is connected between the third pipe section 111 and the fourth pipe section 113.

Of course, the inner ring of the bearing 400 corresponds to the outer ring of the bearing 400. That is, the inner race of the bearing 400 is sleeved on the third pipe section 111, or the inner race of the bearing 400 is sleeved on the bellows section 112, or the inner race of the bearing 400 is sleeved on the fourth pipe section 113, or the inner race of the bearing 400 is sleeved on the third pipe section 111 and the bellows section 112, or the inner race of the bearing 400 is sleeved on the bellows section 112 and the fourth pipe section 113, or the inner race of the bearing 400 is sleeved on the third pipe section 111, the bellows section 112 and the fourth pipe section 113.

Specifically, the number of bearings 400 may be one or more, and when the first pipe section 121 and the second pipe section 122 are sleeved on the outer ring of the bearings 400, the number of bearings 400 is two, and when the first pipe section 121, the hub 320 and the second pipe section 122 are all sleeved on the outer ring of the bearings 400, the number of bearings 400 is two or three.

The combustion chamber according to an embodiment of the present invention comprises the nozzle 10 of any of the embodiments described above.

The gas turbine according to the embodiment of the invention comprises the combustion chamber of any embodiment.

In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings are merely for convenience in describing the present invention and simplifying the description, and do not indicate or imply that the device or element being referred to must have a specific orientation, be configured and operated in a specific orientation, and therefore should not be construed as limiting the present invention.

Furthermore, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include at least one such feature. In the description of the present invention, the meaning of "plurality" means at least two, for example, two, three, etc., unless specifically defined otherwise.

In the present invention, unless explicitly specified and limited otherwise, the terms "mounted," "connected," "secured," and the like are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally formed; may be mechanically connected, may be electrically connected or may be in communication with each other; either directly or indirectly, through intermediaries, or both, may be in communication with each other or in interaction with each other, unless expressly defined otherwise. The specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art according to the specific circumstances.

In the present invention, unless expressly stated or limited otherwise, a first feature "up" or "down" a second feature may be the first and second features in direct contact, or the first and second features in indirect contact via an intervening medium. Moreover, a first feature being "above," "over" and "on" a second feature may be a first feature being directly above or obliquely above the second feature, or simply indicating that the first feature is level higher than the second feature. The first feature being "under", "below" and "beneath" the second feature may be the first feature being directly under or obliquely below the second feature, or simply indicating that the first feature is less level than the second feature.

For purposes of this disclosure, the terms "one embodiment," "some embodiments," "example," "a particular example," or "some examples," etc., mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the invention. In this specification, schematic representations of the above terms are not necessarily directed to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples. Furthermore, the different embodiments or examples described in this specification and the features of the different embodiments or examples may be combined and combined by those skilled in the art without contradiction.

While embodiments of the present invention have been shown and described above, it will be understood that the above embodiments are illustrative and not to be construed as limiting the invention, and that variations, modifications, alternatives and variations may be made to the above embodiments by one of ordinary skill in the art within the scope of the invention.

Claims

1. A nozzle, comprising:

the central body comprises a central pipe and an outer pipe, the central pipe is provided with a duty fuel channel, the outer pipe is sleeved on the central pipe, a part of the outer pipe is rotatably arranged, the outer pipe comprises a first pipe section, the part and a second pipe section, and a premixing fuel channel is defined between the first pipe section and the central pipe;

a swirler comprising vanes and a hub, the vanes being rotatably disposed within the oxygen-containing gas passage, the rotational axis of the vanes being parallel to the direction of extension of the oxygen-containing gas passage, the vanes having fuel passages through which the premix fuel passages communicate with the oxygen-containing gas passage, the portion of the outer tube forming the hub;

the inner ring of the bearing is sleeved on the central tube, and the hub is sleeved on the outer ring of the bearing;

the central tube comprises a third tube section, a corrugated tube section and a fourth tube section which are sequentially connected, and the inner ring of the bearing is sleeved on at least one of the third tube section, the corrugated tube section and the fourth tube section.

2. A nozzle according to claim 1, wherein the rotational axis of the outer tube is parallel to the direction of extension of the oxygen-containing gas channel, said portion of the outer tube being connected to the vanes for rotation of the vanes.

3. The nozzle of claim 2, wherein the first tube segment, the hub and the second tube segment are connected in sequence in an extending direction of a rotational axis of the vane, a center axis of the hub, a center axis of the first tube segment and a center axis of the second tube segment coincide with each other, wherein the hub has a fuel inlet in communication with the premix fuel passage, the vane is provided on the hub, and the fuel inlet and the fuel passage are in communication.

4. A nozzle according to claim 3, wherein the hub and the vanes are integrally formed.

5. The nozzle of any one of claims 1-4, wherein the vanes and shroud are spaced apart in a radial direction of the oxygen-containing gas passage.

6. A combustion chamber, characterized by comprising a nozzle according to any one of claims 1-5.

7. A gas turbine comprising a combustion chamber according to claim 6.