CN118149360A - Peripheral circumferentially staged combustor nozzle, gas turbine and staged control method - Google Patents

Abstract

The invention discloses a peripheral circumferential staged combustion chamber nozzle, a gas turbine and a staged control method, which comprises a central nozzle and a plurality of peripheral nozzles, wherein the peripheral nozzles are arranged on the peripheral side of the central nozzle; the peripheral nozzle comprises a central body and a plurality of blades, and a plurality of fuel pipelines are arranged in the central body; the blades are arranged on the peripheral side of the central body and are arranged at intervals along the circumferential direction of the central body, the blades comprise primary blades, secondary blades and tertiary blades which are respectively communicated with corresponding fuel pipelines, the primary blades and the tertiary blades are oppositely arranged in the radial direction of the central nozzle, the secondary blades are positioned between the primary blades and the tertiary blades, and when the combustor is started, the fuel injection moments of the primary blades, the secondary blades and the tertiary blades are different. The combustion chamber nozzle can avoid the condition of larger temperature difference of the section at the outlet, further improve the adverse effect of the larger temperature difference on the downstream turbine blade, and ensure the service life of the turbine blade.

Description

Peripheral circumferentially staged combustor nozzle, gas turbine and staged control method

Technical Field

The invention relates to the technical field of gas turbines, in particular to a peripheral circumferential staged combustion chamber nozzle, a gas turbine and a staged control method.

Background

A gas turbine is an internal combustion power machine that is used primarily to convert the heat of fuel into useful work. However, in the actual use process, the temperature difference of the section at the outlet of the combustion chamber of the gas turbine is large, the service life of the downstream turbine blade is long, and the long-term stable operation of the gas turbine is not facilitated.

Disclosure of Invention

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

Therefore, the embodiment of the invention provides the peripheral circumferential staged combustion chamber nozzle, which can avoid the condition of larger temperature difference of the section at the outlet, further improve the adverse effect of larger temperature difference on the downstream turbine blades and ensure the service life of the turbine blades.

The embodiment of the invention also provides a gas turbine comprising the peripherally staged combustion chamber nozzle.

The embodiment of the invention also provides a grading control method of the combustion chamber nozzle or the gas turbine based on the peripheral circumferential grading.

The peripheral circumferentially staged combustion chamber nozzle comprises a central nozzle and a plurality of peripheral nozzles, wherein the peripheral nozzles are arranged on the periphery side of the central nozzle and are arranged at intervals along the circumferential direction of the central nozzle;

The peripheral nozzle includes:

The central body is internally provided with a plurality of fuel pipelines;

The blades are arranged on the periphery of the central body and are arranged along the periphery of the central body at intervals, the blades comprise primary blades, secondary blades and tertiary blades which are respectively communicated with the corresponding fuel pipelines, the primary blades and the tertiary blades are oppositely arranged in the radial direction of the central nozzle, the secondary blades are positioned between the primary blades and the tertiary blades, and when the combustor is started, the primary blades, the secondary blades and the tertiary blades are different in fuel injection time.

In some embodiments, the circumference of the central body is divided into a first-stage area, a second-stage area and a third-stage area, the first-stage area and the third-stage area are oppositely arranged in the radial direction of the central nozzle, two second-stage areas are oppositely arranged in the circumferential direction of the central nozzle, the first-stage blades are arranged in the first-stage area, the second-stage blades are arranged in the second-stage area, and the third-stage blades are arranged in the third-stage area.

In some embodiments, the central angle corresponding to the primary region, the central angle corresponding to the secondary region, and the central angle corresponding to the tertiary region are the same.

In some embodiments, the number of primary blades in the primary region, the number of secondary blades in the secondary region, and the number of tertiary blades in the tertiary region are the same.

In some embodiments, a swirler is included for creating a swirl to eliminate temperature differences between a plurality of the peripheral nozzles.

In some embodiments, a plurality of the blades are equally spaced along the circumference of the central body.

In some embodiments, the number of blades is an even number;

and/or the cross section of the peripheral nozzle is circular.

The gas turbine of an embodiment of the invention includes a peripherally staged combustor nozzle as described in any of the embodiments above.

The hierarchical control method of the embodiment of the invention comprises the following steps:

s1: when starting, firstly injecting fuel through a central nozzle;

S2: after the fuel injector runs for a certain period of time, adding all the primary blade injection fuel of the peripheral nozzle, then adding all the secondary blade injection fuel of the peripheral nozzle, and finally adding all the tertiary blade injection fuel of the peripheral nozzle.

In some embodiments, the method further comprises the steps of:

s3: and after the basic load is reached, adjusting the shape of the flame by adjusting the injected fuel quantity of the primary blade, the secondary blade and the tertiary blade so as to realize the adjustment of the thermo-acoustic characteristics.

The beneficial effects are that: according to the combustor nozzle, the gas turbine and the grading control method, the condition that the temperature difference of the section at the outlet is large is avoided, the adverse effect of the large temperature difference on the downstream turbine blade is improved, the service life of the turbine blade is ensured, and the structural stability of the whole operation is further ensured.

Drawings

FIG. 1 is a schematic illustration of a cross-section of a combustor nozzle of an embodiment of the present invention.

FIG. 2 is a schematic illustration of the startup of various nozzles of a combustor nozzle under different load conditions in accordance with an embodiment of the present invention.

Reference numerals:

A central nozzle 1;

A peripheral nozzle 2; a first level region 21; a secondary region 22; a tertiary zone 23.

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.

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

In the related art, in order to ensure that the combustion chamber of the gas turbine can work normally at the time of increasing the rotational speed, the low load point and the base load, the nozzles of the combustion chamber of the gas turbine are generally designed with an intermediate nozzle and a peripheral nozzle, wherein the peripheral nozzle is generally provided with a plurality of peripheral nozzles and is arranged at intervals in the circumferential direction of the intermediate nozzle. When the engine operates under a low-load working condition, only part of peripheral nozzles perform fuel injection, so that a large temperature difference exists between the peripheral nozzles which are operated and the peripheral nozzles which are not operated, the temperature difference causes the problem of large temperature difference of an outlet temperature profile, and the service life of the downstream blade is easily influenced.

The peripheral circumferentially staged combustor nozzle (hereinafter referred to as combustor nozzle) of the embodiment of the present invention includes a central nozzle 1 and a plurality of peripheral nozzles 2, C in fig. 1 may denote the central nozzle 1, and the plurality of peripheral nozzles 2 are all disposed on the circumferential side of the central nozzle 1 and are arranged at intervals along the circumferential direction of the central nozzle 1.

For example, as shown in fig. 1, the peripheral nozzles 2 may be provided with six, and the six peripheral nozzles 2 may be arranged at equal intervals along the circumferential direction of the center nozzle 1. In other embodiments, the number of peripheral nozzles 2 may be four, five, seven, eight, etc.

The peripheral nozzle 2 comprises a central body and a plurality of blades, wherein the central body can be in a cylindrical shape, and a plurality of fuel pipelines are arranged in the central body and used for supplying fuel to pass through, so that the conveying requirement of the fuel supply can be met.

The blades are arranged on the peripheral side of the central body and are arranged at intervals along the circumferential direction of the central body, the blades comprise primary blades, secondary blades and tertiary blades which are respectively communicated with corresponding fuel pipelines, the primary blades and the tertiary blades are oppositely arranged in the radial direction of the central nozzle 1, and the secondary blades are positioned between the primary blades and the tertiary blades.

For example, each vane may extend generally along a radial direction of the central body, and the plurality of vanes may be arranged at equal intervals along a circumferential direction of the central body, each vane may be provided with a plurality of fuel injection holes, and each fuel injection hole on each vane may be connected to a corresponding fuel pipe, so that fuel injection may be performed through the fuel injection holes.

It should be noted that, the plurality of blades on each peripheral nozzle 2 may be divided into three types according to the sequence of injecting fuel, and the three types of blades are a first-stage blade, a second-stage blade and a third-stage blade, where the first-stage blade may be located at a side of the peripheral nozzle 2 facing the central nozzle 1, the third-stage blade may be located at a side of the peripheral nozzle 2 facing away from the central nozzle 1, and the second-stage blade may be located between the first-stage blade and the third-stage blade.

When the burner is started, the fuel injection time of the primary blade, the secondary blade and the tertiary blade is different. Specifically, in the low load condition, after the central nozzle 1 is injected with fuel and ignited, the central nozzle may be injected with fuel and ignited by the first stage blade, then may be injected with fuel and ignited by the second stage blade, and finally may be injected with fuel and ignited by the third stage blade.

In other embodiments, fuel may be injected and ignited by the secondary lobes first, then by the primary lobes, and finally by the tertiary lobes. That is, the order of fuel injection of the primary blade, the secondary blade and the tertiary blade can be adjusted according to the use requirement.

It should be noted that the number of fuel pipes of each peripheral nozzle 2 may be the same as the number of stages of the plurality of vanes, for example, when the plurality of vanes are divided into a primary vane, a secondary vane and a tertiary vane, the number of fuel pipes in the central body may be only three, and the three fuel pipes are respectively communicated with the primary vane, the secondary vane and the tertiary vane, thereby satisfying the use requirement of separately delivering fuel into each stage of vanes.

In the combustion chamber nozzle provided by the embodiment of the invention, during a low-load working condition, part of blades of all peripheral nozzles 2 can inject fuel and ignite simultaneously, and then all the blades of all the peripheral nozzles 2 inject fuel and ignite in a step-by-step adding mode. By adopting the combustion starting mode, all the peripheral nozzles 2 run simultaneously under different load working conditions, so that the temperatures of all the peripheral nozzles 2 are approximately consistent, the situation that the temperature difference between the peripheral nozzles 2 in two different working condition states is large when part of the peripheral nozzles 2 in the working part of the peripheral nozzles 2 do not work in the prior art is avoided, the problem that the large temperature difference has a large influence on downstream turbine blades is avoided, and the service life of the downstream turbine blades is ensured.

In some embodiments, the peripheral side of the central body is divided into a primary region 21, a secondary region 22 and a tertiary region 23, the primary region 21 and the tertiary region 23 being arranged opposite to each other in the radial direction of the central nozzle 1, the secondary region 22 being two, and the two secondary regions 22 being arranged opposite to each other in the circumferential direction of the central nozzle 1.

For example, as shown in fig. 1, the space region on the peripheral side of the central body may be divided into four regions, each of which is a substantially quarter sector region. The fan-shaped area close to the central nozzle 1 is a primary area 21, namely an area denoted by the reference number O1 in fig. 1, and the fan-shaped area opposite to the primary area 21 and far from the central nozzle 1 is a tertiary area 23, namely an area denoted by the reference number O3 in fig. 1. The two sector areas, which are arranged opposite each other in the circumferential direction of the central nozzle 1 and are located between the primary area 21 and the tertiary area 23, respectively, are then both secondary areas 22, i.e. areas marked O2 in fig. 1. The first-stage blades are arranged in the first-stage area 21, the second-stage blades are arranged in the second-stage area 22, and the third-stage blades are arranged in the third-stage area 23, so that the classification of a plurality of blades is facilitated.

In some embodiments, the central angle corresponding to the primary region 21, the central angle corresponding to the secondary region 22, and the central angle corresponding to the tertiary region 23 are the same. For example, as shown in fig. 1, the primary region 21, the secondary region 22 and the tertiary region 23 may be substantially quarter sector regions, that is, the central angle corresponding to each region may be 90 degrees.

In other embodiments, the central angle corresponding to the primary region 21 may be the same as the central angle corresponding to the tertiary region 23 only, and the central angle corresponding to the secondary region 22 may be different from the central angle of the primary region 21 or the tertiary region 23.

For example, the sum of the central angles corresponding to the two secondary areas 22 may be the same as the central angle corresponding to the primary area 21 or the tertiary area 23, and when a plurality of vanes are arranged at equal intervals along the circumferential direction of the central body, the distribution density of the vanes in each area may be made the same, so that the quantity of injected fuel of each stage of vanes may be made substantially uniform, thereby facilitating the overall stability of staged ignition.

In some embodiments, the number of primary blades in primary region 21, the number of secondary blades in secondary region 22, and the number of tertiary blades in tertiary region 23 are the same. The quantity of injected fuel of each stage of blades can be made to be approximately uniform, and the integral stability of staged ignition is further ensured.

In some embodiments, the combustor nozzle includes a swirler for creating a swirl to eliminate temperature differences between the plurality of peripheral nozzles 2. For example, at least part of the swirler may be located on the outer peripheral side of the plurality of peripheral nozzles 2, and in use, the swirler may be rotated so that swirling flow may be generated and high temperature gases or the like generated by the plurality of peripheral nozzles 2 may be mixed, further eliminating temperature differences between different peripheral nozzles 2 and further reducing adverse effects on downstream turbine blades.

In some embodiments, the number of blades is an even number. Thereby facilitating equal division of the plurality of blades in different regions.

In some embodiments, as shown in fig. 1, the peripheral nozzle 2 is circular in cross-section.

The following describes a gas turbine according to an embodiment of the present invention.

The gas turbine of an embodiment of the invention includes a combustor nozzle, which may be a combustor nozzle as described in any of the embodiments above. The combustion chamber of the gas turbine can also comprise a combustion pressure cylinder, a guide bush, a hood, a combustion chamber head, a flame tube, a transition section and the like, when the gas turbine is operated, air is compressed into high-pressure air by a gas compressor, then enters the combustion pressure cylinder from a diffuser, enters the combustion chamber head through an annular channel formed by the guide bush and the flame tube, enters a nozzle (which can be regarded as a combustion chamber nozzle) at the combustion chamber head after the combustion chamber head is folded, is mixed with fuel in the nozzle, then enters the flame tube, and finally can be sprayed into a turbine through the transition section and push turbine blades to do work.

The hierarchical control method of the embodiment of the present invention is described below.

The hierarchical control method of the embodiment of the invention comprises the following steps:

S1: at start-up, fuel is first injected through the central nozzle 1. Specifically, at the time of starting the gas turbine, fuel may be injected into the center nozzle 1 first, so that the center nozzle 1 is ignited first.

S2: after a certain period of operation, the fuel is injected by adding all the primary blades of the peripheral nozzles 2, then the fuel is injected by adding all the secondary blades of the peripheral nozzles 2, and finally the fuel is injected by adding all the tertiary blades of the peripheral nozzles 2.

Specifically, as shown in fig. 2, after the central nozzle 1 completes ignition, the load 1 is in a working mode in which only the central nozzle 1 injects fuel. Then, fuel can be introduced into each one-stage blade of all the peripheral nozzles 2 at first, so that ignition of each one-stage blade can be realized, and the ignition is performed at the moment, namely in a working condition mode of the load 2, and in the mode, fuel is injected into all the one-stage blades of the central nozzle 1 and all the peripheral nozzles 2.

Then, fuel can be introduced into all the secondary blades of all the peripheral nozzles 2, so that the ignition of each secondary blade can be realized, and the central nozzle 1, all the primary blades and all the secondary blades are injected with fuel in the working condition mode of the load 3. Finally, fuel can be introduced into all three-stage blades of all peripheral nozzles 2, so that ignition of all three-stage blades can be realized, and the ignition is in a working condition mode of a load 4.

After the central nozzle 1, all the first-stage blades, all the second-stage blades and all the third-stage blades are kept to inject fuel and run for a period of time, the central nozzle 1, all the first-stage blades, all the second-stage blades and all the third-stage blades can be regarded as a working condition mode of running to a basic load at the moment, and the central nozzle 1, all the first-stage blades, all the second-stage blades and all the third-stage blades keep to inject fuel in the mode.

This manner of injecting fuel and igniting in a radial direction of the fuel nozzle and along a step from the center to the outside can enable the portion of the next stage ignition to be ignited by the partial flame of which the inside has been ignited, thereby ensuring the stability of ignition.

In some embodiments, the hierarchical control method further comprises the steps of:

S3: after the basic load is reached, the shape of the flame is adjusted by adjusting the injected fuel quantity of the primary blade, the secondary blade and the tertiary blade so as to realize the adjustment of the thermo-acoustic characteristics. For example, in the operation process, the fuel quantity injected by the secondary blade can be regulated to be different from that of the primary blade or the tertiary blade, so that the integral flame shape can be regulated, and the problems of concentrated flame and high thermoacoustic oscillation risk caused by the same flame position at each nozzle are avoided.

The beneficial effects are that: according to the combustor nozzle, the gas turbine and the grading control method, the peripheral nozzles 2 are locally subjected to circumferential grading, so that the purpose of locally controlling the equivalent ratio of the peripheral nozzles 2 can be achieved, on one hand, when partial load is carried out, the local blades of the peripheral nozzles 2 are sprayed with fuel, but all the peripheral nozzles 2 are sprayed with fuel, after the peripheral nozzles 2 are locally combusted, the problem of large temperature difference among the peripheral nozzles 2 can be further solved through the cyclone effect of the cyclone, and the temperature difference of the outlet temperature profile is small, so that the influence on the service life of downstream turbine blades is small; on the other hand, the thermoacoustic characteristics can be adjusted by adjusting the shape of the local flame of the nozzle under the basic load working condition, so that the situation of high thermoacoustic oscillation risk is avoided.

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 the above embodiments have been shown and described, it should be understood that the above embodiments are illustrative and not to be construed as limiting the invention, and that variations, modifications, alternatives, and variations of the above embodiments may be made by those of ordinary skill in the art without departing from the scope of the invention.

Claims (10)

1. A peripherally staged combustion chamber nozzle comprising a central nozzle and a plurality of peripheral nozzles, the plurality of peripheral nozzles being disposed circumferentially of the central nozzle and being spaced apart along the circumference of the central nozzle;

The peripheral nozzle includes:

The central body is internally provided with a plurality of fuel pipelines;

The blades are arranged on the periphery of the central body and are arranged along the periphery of the central body at intervals, the blades comprise primary blades, secondary blades and tertiary blades which are respectively communicated with the corresponding fuel pipelines, the primary blades and the tertiary blades are oppositely arranged in the radial direction of the central nozzle, the secondary blades are positioned between the primary blades and the tertiary blades, and when the combustor is started, the primary blades, the secondary blades and the tertiary blades are different in fuel injection time.

2. The peripherally staged combustor nozzle of claim 1, wherein the peripheral side of the centerbody is divided into a primary region, a secondary region and a tertiary region, the primary region and the tertiary region being disposed opposite each other in a radial direction of the centerbody, the secondary region being disposed opposite each other in a peripheral direction of the centerbody, the primary vanes being disposed in the primary region, the secondary vanes being disposed in the secondary region, the tertiary vanes being disposed in the tertiary region.

3. The peripherally staged combustion chamber nozzle of claim 2, wherein said primary region has a common central angle, said secondary region has a common central angle, and said tertiary region has a common central angle.

4. The peripherally staged combustor nozzle of claim 2, wherein the number of primary vanes in said primary zone, the number of secondary vanes in said secondary zone, and the number of tertiary vanes in said tertiary zone are the same.

5. The peripherally staged combustor nozzle of claim 1, including a swirler for creating a swirling flow to eliminate temperature differences between a plurality of said peripheral nozzles.

6. The peripherally staged combustor nozzle of any of claims 1-5, wherein a plurality of said vanes are equally spaced circumferentially along said central body.

7. The peripherally staged combustor nozzle of claim 6, wherein said vanes are an even number;

and/or the cross section of the peripheral nozzle is circular.

8. A gas turbine comprising a peripherally staged combustor nozzle as claimed in any one of the preceding claims 1-7.

9. A staged control method of a combustion chamber nozzle based on peripheral circumferential staging according to any one of the preceding claims 1-7 or a gas turbine according to claim 8, characterized by comprising the steps of:

s1: when starting, firstly injecting fuel through a central nozzle;

S2: after the fuel injector runs for a certain period of time, adding all the primary blade injection fuel of the peripheral nozzle, then adding all the secondary blade injection fuel of the peripheral nozzle, and finally adding all the tertiary blade injection fuel of the peripheral nozzle.

10. The hierarchical control method according to claim 9, characterized by further comprising the steps of:

s3: and after the basic load is reached, adjusting the shape of the flame by adjusting the injected fuel quantity of the primary blade, the secondary blade and the tertiary blade so as to realize the adjustment of the thermo-acoustic characteristics.