CN116624891A - Gas turbine engine, mixer assembly, combustor for the same, and method of atomizing fuel - Google Patents

Abstract

The application relates to a gas turbine engine and a mixer assembly, a combustion chamber and a method for atomizing fuel for the same. Wherein the mixer assembly for a gas turbine engine comprises: a main combustion mixer comprising: an annular inner wall; an annular outer wall forming an annular chamber around at least a portion of the annular inner wall; the plurality of fuel spray holes at least comprise a first fuel spray hole and a second fuel spray hole, wherein the first fuel spray hole is positioned on the annular inner wall, the first fuel spray hole is provided with a first spray direction, the first spray direction points to the annular outer wall, the second fuel spray hole is positioned on the annular outer wall, the second fuel spray hole is provided with a second spray direction, and the second spray direction points to the annular inner wall.

Description

Gas turbine engine, mixer assembly, combustor for the same, and method of atomizing fuel

Technical Field

The present application relates to the field of gas turbine engines, and more particularly to a gas turbine engine and a mixer assembly, a combustor, and a method of atomizing fuel for the same.

Background

The increased environmental awareness has made the reduction of pollutant emissions during combustion one of the major challenges in aircraft engine development. In order to achieve lower NOx emissions without increasing the concentration of tail gas carbon monoxide and unburned hydrocarbons, low emission combustion forms utilizing lean premixed pre-vaporization and rich quenched lean combustion have been widely studied and used in gas turbines and aircraft engines. However, as aircraft engines move toward higher pressure ratios, higher inlet pressures and temperatures of the combustion chamber present new challenges for efficient low pollution combustion organizations.

The inventors of the present application have found that for high pressure ratio aircraft engines, the auto-ignition firing time of the fuel is reduced due to the increased temperature and pressure at its inlet, and that existing lean premixed combustion carries the risk of flashback and auto-ignition.

Disclosure of Invention

It is an object of the present application to provide a mixer assembly for a gas turbine engine.

It is a further object of the present application to provide a combustor for a gas turbine engine.

It is a further object of the present application to provide a gas turbine engine.

It is a further object of the present application to provide a method of atomizing fuel for a gas turbine engine.

A mixer assembly for a gas turbine engine according to one aspect of the application is characterized by comprising: a main combustion mixer comprising: an annular inner wall; an annular outer wall forming an annular chamber around at least a portion of the annular inner wall; the plurality of fuel spray holes at least comprise a first fuel spray hole and a second fuel spray hole, wherein the first fuel spray hole is positioned on the annular inner wall, the first fuel spray hole is provided with a first spray direction, the first spray direction points to the annular outer wall, the second fuel spray hole is positioned on the annular outer wall, the second fuel spray hole is provided with a second spray direction, and the second spray direction points to the annular inner wall.

According to the technical scheme, through the structure that the first injection direction points to the annular outer wall and the second injection direction points to the annular inner wall, the opposite injection of the fuel of the main combustion mixer is realized, so that the annular main combustion grade fuel is easy to atomize and quickly mix with air after mutually colliding, the advantages of reducing risks of spontaneous combustion, tempering and unstable combustion of direct injection relative to premixed combustion are maintained, and meanwhile, the method also has the advantage of uniform mixing of the fuel and the air.

Meanwhile, the structure of the annular chamber enables the main combustion stage flame to be an integral annular flame, and the defect of uneven temperature distribution caused by flame coupling interference existing in a plurality of independent main combustion stages distributed in an array mode is avoided.

In one or more embodiments of the mixer assembly, the axial position of the first fuel injection orifice is the same as the axial position of the second fuel injection orifice.

In one or more embodiments of the mixer assembly, the first spray direction is opposite the second spray direction.

In one or more embodiments of the mixer assembly, at least one of the annular inner wall and the annular outer wall has a first constriction, the flow area of the annular chamber decreasing in an upstream to downstream direction through the first constriction.

In one or more embodiments of the mixer assembly, the downstream of the constriction has an expansion structure through which the flow area of the annular chamber increases from the upstream to the downstream direction.

In one or more embodiments of the mixer assembly, the expansion structure extends axially to a downstream end of the annular chamber, and the first contraction structure extends axially to an upstream end of the expansion structure.

In one or more embodiments of the mixer assembly, the axial position of the fuel injection orifice is located between the axial positions of the first contracted structure and the expanded structure.

In one or more embodiments of the mixer assembly, the axial position of the fuel nozzle is from 20mm to 30mm from the downstream outlet of the annular chamber.

In one or more embodiments of the mixer assembly, the mixer assembly further includes a fuel line fluidly connected to the fuel orifice.

In one or more embodiments of the mixer assembly, a first swirler is disposed in the annular chamber, the axial position of the first swirler being located in an upstream section of the annular chamber and the axial position of the fuel injection holes being located in a downstream section of the annular chamber.

In one or more embodiments of the mixer assembly as defined in any one of the preceding claims, a precombustion mixer is included, at least part of which is surrounded by the main combustion mixer, the precombustion mixer comprising an annular body having an outer surface that constitutes an annular inner wall of the main combustion mixer.

In one or more embodiments of the mixer assembly, the annular body has an inner surface with a second constriction, the axial position of the second constriction being upstream of the first constriction of the main combustion mixer.

According to another aspect of the application, a combustor for a gas turbine engine comprises: a combustion vessel; and the mixer assembly of any of claims disposed adjacent the combustion vessel, a downstream end of the annular chamber of the mixer assembly being in direct communication with the combustion vessel, configured to provide a flow of a mixture of fuel and air to the combustion vessel.

A gas turbine engine according to yet another aspect of the application comprises a combustion chamber as described above.

A method for atomizing fuel for a gas turbine engine according to yet another aspect of the present application includes: providing a primary mixer, the primary mixer being arranged to: fuel is injected into the main mixer through a first fuel orifice located at an annular inner wall of the main mixer and a second fuel orifice located at an annular outer wall of the main mixer, wherein the fuel is atomized by collision of a first fuel stream injected by the first fuel orifice with a second fuel stream injected by the second fuel orifice.

Drawings

The above and other features, properties and advantages of the present application will become more apparent from the following description of the accompanying drawings and embodiments in which like reference numerals refer to like features throughout, it being noted that these drawings are given by way of example only, which are not drawn to scale and should not be construed to limit the true scope of the application, wherein:

FIG. 1 is a schematic view of a combustion chamber according to an embodiment;

FIG. 2 is a schematic view showing a part of the structure of a main combustion mixer according to an embodiment;

FIG. 3 is a cross-sectional view A-A of a schematic structural diagram of the combustion chamber according to FIG. 1, in accordance with one embodiment.

Reference numerals:

1000-combustion chamber;

a 100-mixer assembly;

10-a main combustion mixer;

1-an annular inner wall, 2-an annular outer wall;

101-an annular chamber, 1011-an upstream section, 1012-a downstream section, 1013-a downstream end;

102-a first contracted configuration, 103-an expanded configuration, 1031-an upstream end;

3-fuel injection hole, 31-first fuel injection hole, 32-second fuel injection hole, D1-first injection direction, D2-second injection direction;

4-fuel line, 41-first fuel line, 42-second fuel line;

5-a primary gas-liquid mixture;

51-first swirler, 52-main combustion stage flame;

20-precombustion mixer. 201. 202-an annular combustion channel;

21-an annular body, 211-an outer surface, 212-an inner surface, 213-a second contracted configuration, 214-a second expanded configuration;

22-centrifugal nozzle, 23-second cyclone, 24-third cyclone;

6-spraying droplets;

13-precombustion stage flame;

200-combustion vessel;

16-high temperature gas.

DETAILED DESCRIPTION OF EMBODIMENT (S) OF INVENTION

Reference will now be made in detail to the various embodiments of the application, examples of which are illustrated in the accompanying drawings and described below. While the application will be described in conjunction with the exemplary embodiments, it will be appreciated that the present description is not intended to limit the application to those exemplary embodiments. On the contrary, the application is intended to cover not only these exemplary embodiments, but also various alternatives, modifications, equivalents and other embodiments, which may be included within the spirit and scope of the application as defined by the appended claims.

In the description that follows, references to orientations or positional relationships that are indicated by "axial," "radial," "circumferential," "inner," "outer," "upstream," "downstream," or other azimuthal terms are based on the orientation or positional relationships shown in the drawings, are merely for convenience in describing the application and simplifying the description, and do not indicate or imply that the devices or components referred to must have a particular orientation, be configured and operated in a particular orientation, and therefore should not be construed as limiting the application. In addition, "upstream" and "downstream" are distinguished based on the direction in which the air flows, specifically, the air flows from "upstream" to "downstream".

Meanwhile, the present application uses specific words to describe embodiments of the present application. Reference to "one embodiment" and/or "an embodiment" means that a particular feature, structure, or characteristic is associated with at least one embodiment of the application. Thus, it should be emphasized and should be appreciated that two or more references to "an embodiment" or "one embodiment" in various positions in this specification are not necessarily referring to the same embodiment. Furthermore, certain features, structures, or characteristics of one or more embodiments of the application may be combined as suitable.

Currently, as aircraft engines move toward higher pressure ratios, higher inlet pressures and temperatures for the combustion chamber place higher demands on efficient and low pollution combustion organizations.

The inventor of the present application has conducted intensive studies to find that for a high pressure ratio aeroengine, the autoignition firing time of the fuel is shortened due to the increase of the temperature and pressure of the inlet thereof, and the existing lean premixed combustion brings about the risks of flashback and autoignition.

Lean direct injection techniques form a flame by injecting fuel directly into the combustion chamber and blending air for a very short period of time. This combustion organization may be at a reduced NOx pollutant emissions.

In a comparison of lean direct injection combustor configurations, radially staged lean direct injection combustors, the precombustion stage flame is still generally diffusion-type, while the main stage is lean direct injection combustion formed by a plurality of swirlers, the main stage being in an array-type arrangement, i.e., a plurality of independent main stages are circumferentially arranged. The inventor found that this comparison solution, although solving the fuel regulation problem of the lean direct injection combustor, has the problems that the main combustion stage is independent, the formed flames have mutual coupling interference, a local high-temperature area is easy to form at the downstream of the combustor, the temperature distribution is not uniform enough, difficulties are caused to further reduce pollutant emission and improve the uniformity of the temperature distribution at the inlet of the turbine, and the local high-temperature area also causes the risk of backfire and spontaneous combustion due to unstable local flow.

Based on the above considerations, the inventor has conducted intensive studies to design a mixer assembly for a gas turbine engine, and through the structure that the first injection direction is directed to the annular outer wall and the second injection direction is directed to the annular inner wall, the hedging injection of the main combustion mixer fuel is realized, so that the annular main combustion grade fuel is easy to atomize and rapidly mix with air due to mutual collision, the advantage of reducing risks of spontaneous combustion, tempering and unstable combustion in direct injection relative to premixed combustion is maintained, and meanwhile, the mixer assembly also has the advantage of uniformly mixing the fuel and the air.

In addition, the structure of the annular chamber enables the main combustion stage flame to be an integral annular flame, so that the defect of uneven temperature distribution caused by flame coupling interference existing in a plurality of independent main combustion stages distributed in an array mode in a comparison scheme is avoided, and the risks of backfire and spontaneous combustion caused by unstable local flow in a local high-temperature area are avoided.

Although the embodiments of the present application disclose a mixer assembly suitable for use in a gas turbine engine, such as an aero-engine, the application is not limited thereto, and may be, for example, a marine gas turbine, a ground gas turbine, etc.

In the following description, "fuel" is exemplified by aviation fuel, that is, aviation kerosene, but not limited thereto, and any fuel that requires atomization may be applied to the mixer assembly described in the embodiments.

Referring to FIG. 1 in conjunction with FIG. 3, in one embodiment, a specific configuration of a mixer assembly 100 for a gas turbine engine may be that including a main combustion mixer 10. The main combustion mixer 10 comprises an annular inner wall 1, an annular outer wall 2 and a plurality of fuel injection holes 3. The annular outer wall 2 forms an annular chamber 101 around at least part of the annular inner wall 1. The plurality of fuel injection holes 3 at least comprises a first fuel injection hole 31 and a second fuel injection hole 32, the first fuel injection hole 31 is located at the annular inner wall 1, the first fuel injection hole 31 has a first injection direction D1, the first injection direction D1 is directed toward the annular outer wall 2, the second fuel injection hole 32 is located at the annular outer wall 2, the second fuel injection hole 32 has a second injection direction D2, and the second injection direction D2 is directed toward the annular inner wall 1.

The meaning of "the first injection direction D1 is directed to the annular outer wall 2" and "the second injection direction D2 is directed to the annular inner wall 1", and the meaning of "the direction" is not limited to the vertical direction, and the injection direction is directed to the annular wall surface, and the angle between the injection direction and the annular wall surface is not particularly limited, and the first injection direction D1 and the second injection direction D2 are directed to the annular outer wall 2 and the annular inner wall 1, respectively, and are directed to the same downstream direction (the combustion vessel 200) at the same time, because the direct injection combustion chamber technology is adopted, for example, as shown in fig. 2.

The plurality of fuel injection holes 3 include at least a first fuel injection hole 31 and a second fuel injection hole 32, and herein, the meaning of "at least" is that the first fuel injection hole 31 and the second fuel injection hole 32 are a group, and the plurality of fuel injection holes 3 may include a plurality of groups of "first fuel injection hole 31 and second fuel injection hole 32", which are uniformly arranged in the circumferential direction of the annular inner wall 1 and the annular outer wall 2 to form a circumferentially uniform main combustion stage direct injection flame, and typically the number of groups is 12-36, for example, as shown in fig. 3, 12 groups of the first fuel injection hole 31 and the second fuel injection hole 32 are uniformly arranged in the circumferential direction of the annular inner wall 1 and the annular outer wall 2.

The beneficial effects that so set up lie in, through the directional annular outer wall of first injection direction, the directional annular inner wall of second injection direction's structure, realize the hedging injection of main combustion mixer fuel, make annular main combustion grade fuel collide each other and easily atomize and air mix fast, both remain direct injection and reduce the spontaneous combustion for premixed combustion, tempering and the risk that the unstable emergence of burning, the advantage of fuel and air misce bene has simultaneously, its principle lies in, because hedging injection makes the fuel spout form each other and atomizes, the particle diameter of atomizing is less, component distribution is even, the homogeneity of fuel and air mix fast has been guaranteed, the homogeneity of fuel distribution has also guaranteed the homogeneity of combustion temperature field, thereby improve gas turbine engine's turbine inlet temperature distribution homogeneity.

In addition, the structure of the annular chamber enables the main combustion stage flame to be an integral annular flame, so that the defect of uneven temperature distribution caused by flame coupling interference existing in a plurality of independent main combustion stages distributed in an array mode in a comparison scheme is avoided, and the risks of backfire and spontaneous combustion caused by unstable local flow in a local high-temperature area are avoided.

Referring to fig. 1, in some embodiments, the fuel injection hole 3 may have a specific structure in which the axial position of the first fuel injection hole 31 is the same as the axial position of the second fuel injection hole 32.

The term "axially positioned identically" as used herein means that the first fuel injection hole 31 and the second fuel injection hole 32 are disposed radially opposite each other, for example, as shown in fig. 1, and the second fuel injection hole 32 is disposed radially opposite the first fuel injection hole 31.

The beneficial effect that so set up lies in, simple structure is compact, is convenient for form two opposite spray jet of direction.

Referring to fig. 2 in combination with fig. 3, in some embodiments, the specific structure of the fuel injection hole 3 may be that the first injection direction D1 is opposite to the second injection direction D2.

The term "opposed" as used herein means that the first injection direction D1 and the second injection direction D2 may overlap in the radial direction so that the spray jets emitted from the first fuel injection holes 31 and the second fuel injection holes 32 can collide with each other to be atomized and evaporated rapidly.

The beneficial effect that so set up lies in, first injection direction D1 is relative with second injection direction D2, can effectively form the opposite spray efflux, and the spray efflux of being spouted by first fuel orifice 31 and second fuel orifice 32 can collide mutually promptly, and quick atomizing evaporation avoids the flame to take place the coupling interference, makes turbine import temperature distribution even, and then promotes combustion stability.

Referring to fig. 1 in conjunction with fig. 2, in some embodiments, the mixer assembly 100 may be specifically configured such that at least one of the annular inner wall 1 and the annular outer wall 2 has a first constriction 102, and the flow area of the annular chamber 101 decreases from the upstream direction to the downstream direction through the first constriction 102.

The beneficial effect that so set up lies in, the air current can accelerate through first contraction structure for fuel and air mix more rapidly, can effectively prevent the tempering, improve the stability of burning.

With continued reference to fig. 1 in conjunction with fig. 2, in some embodiments, the particular configuration of the mixer assembly 100 may be such that the downstream of the first constriction 102 has an expansion 103, and the flow area of the annular chamber 101 increases from the upstream to the downstream direction through the expansion 103.

The flow area of the annular chamber 101 is specifically reduced from upstream to downstream through the first constriction structure 102 and then expanded through the expansion structure 103, for example, as shown in fig. 2, the nozzle hole 3 is located at the junction between the first constriction structure 102 and the expansion structure 103, and the flow area of the annular chamber 101 is the smallest at the position of the nozzle hole 3.

The beneficial effect that so set up lies in that the air current is through the first shrink structure after accelerating, the flow area of orifice 3 injection position annular chamber 101 is minimum, this position air current velocity of flow is the biggest, and the fuel can be taken away the mixture fast by the air to prevent spontaneous combustion, tempering, improve combustion stability, then through expanding structure with the air current have certain expansion angle, can make the distribution of air-fuel spray's mixture more reasonable, the mixture obtains abundant even burning, reduce pollutant emission, further improve the homogeneity of burning temperature field, thereby improve gas turbine engine's turbine inlet temperature distribution homogeneity.

With continued reference to fig. 1 in conjunction with fig. 2, in some embodiments, the particular configuration of the mixer assembly 100 may be such that the expanding structure 103 extends axially to the downstream end 1013 of the annular chamber 101 and the first contracting structure 102 extends axially to the upstream end 1031 of the expanding structure 103. The beneficial effect of this arrangement is that the air flow accelerated by the first constriction 102 is decelerated in time by the expansion 103 to ensure adequate combustion.

Referring to FIG. 2, in some embodiments, the particular configuration of the mixer assembly 100 may be such that the axial position of the fuel injection orifices 3 is located between the axial positions of the first contracted structure 102 and the expanded structure 103.

"axial position of the fuel injection hole 3", specifically, for example, as shown in fig. 2, the fuel injection hole 3 is located at the junction of the first contracted structure 102 and the expanded structure 103, that is, at the position where the flow area of the annular chamber 101 is minimum.

The beneficial effect that so set up lies in, the air current is through the spraying mix of first constriction structure acceleration and fuel orifice, prevents the tempering, and the back is slowed down through the expansion structure 103, makes the burning more abundant, and the axial position of fuel orifice 3 is located between the axial position of first constriction structure 102 and expansion structure 103, can make the effect of preventing the tempering better and the burning also more abundant, more effective reduction pollution discharge.

With continued reference to FIG. 2, in some embodiments, the particular configuration of the mixer assembly 100 may be such that the axial position of the fuel injection orifices 3 is 20mm-30mm from the axial distance of the downstream outlet of the annular chamber 101. The beneficial effect that so set up lies in, can effectively prevent taking place spontaneous combustion, tempering in the annular cavity, improves combustion stability. The principle is that the spray jet ejected from the first spray hole 31 and the second fuel spray hole 32 can collide with each other, so that the spray jet can be atomized and evaporated quickly, and the fuel does not need to be fully mixed with the air by means of a longer mixing distance and mixing time before reaching a downstream outlet, so that the fuel spray hole 3 can be arranged at a position close to the downstream outlet, spontaneous combustion and tempering in the annular chamber are prevented, and the combustion stability is improved.

Referring to FIG. 1, in some embodiments, the particular configuration of the mixer assembly 100 may also include a fuel line 4, the fuel line 4 being fluidly connected to the fuel injection orifice 3. Here, "fluidly connected" means that fuel is delivered to the fuel injection holes 3 through the fuel line 4 and is injected through the fuel injection holes 3. The structure is simple and the manufacture is convenient.

Referring to fig. 1 in conjunction with fig. 2, in some embodiments, the annular chamber 101 may be specifically configured such that the annular chamber 101 is provided with a first swirler 51, an axial position of the first swirler 51 is located in an upstream section 1011 of the annular chamber 101, and an axial position of the fuel injection holes 3 is located in a downstream section 1012 of the annular chamber 101. The first swirlers 51 are arranged in one-to-one correspondence with the fuel spray holes 3, and in the flowing process of the air flowing through the first swirlers 51, for example, as shown in fig. 1 and 2, the air a passing through the first swirlers 51 passes through the first contraction structure 102, is quickly mixed and evaporated with the liquid mist of the opposite spray jet ejected from the first spray direction D1 and the second spray direction D2 at the fuel spray holes 3, and forms a gas-liquid mixture 5 in the expansion structure 103 to enter the combustion chamber 200, so as to realize the direct-injection main combustion flame 52.

In some embodiments, as shown in fig. 2, the opposite spray jets ejected in the first and second injection directions D1 and D2 are respectively supplied with fuel from the first and second fuel pipelines 41 and 42, and the opposite spray jets ejected in the first and second injection directions D1 and D2 form the gas-liquid mixture 5 with a certain rotation direction and opening angle under the action of the air a passing through the first cyclone 51.

Referring to FIG. 1 in conjunction with FIG. 3, in some embodiments, a specific configuration of mixer assembly 100 may also include pre-combustion mixer 20. At least part of pre-combustion mixer 20 is surrounded by main combustion mixer 10, pre-combustion mixer 20 comprising an annular body 21, annular body 21 having an outer surface 211, outer surface 211 constituting annular inner wall 1 of main combustion mixer 10.

"at least a portion of precombustion mixer 20 is surrounded by main combustion mixer 10", specifically, a portion of precombustion mixer 20 is located radially inward of main combustion mixer 10.

The beneficial effects of setting like this lie in, form radial staged combustion mode, can carry out nimble regulation to the fuel according to different operating modes, cooperate lean oil direct injection burning simultaneously, reach high-efficient stable low pollution burning.

In some embodiments, as shown in fig. 3, main combustion mixer 10 and pre-combustion mixer 20 are concentrically arranged, main combustion mixer 10 surrounds pre-combustion mixer 20, and the overall structure is uniform and compact.

Referring to fig. 1 in conjunction with fig. 2, in some embodiments, the particular configuration of the annular body 21 may be such that the annular body 21 has an inner surface 212, the inner surface 212 having a second constriction 213, the axial position of the second constriction 213 being upstream of the first constriction 102 of the main combustion mixer 10.

In some embodiments, as shown in fig. 1, pre-combustion mixer 20 includes a centrifugal nozzle 22, a second swirler 23, and a third swirler 24, second swirler 23, third swirler 24, and centrifugal nozzle 22 are disposed radially inside annular body 21 in order from outside to inside, centrifugal nozzle 22 is disposed at the center of annular body 21, third swirler 24 is disposed radially outside centrifugal nozzle 22, third swirler 24 is disposed radially inside second swirler 23, and third swirler 24 are disposed at an axial position offset, second swirler 23 is disposed downstream of third swirler 24.

The air flowing through the second and third cyclones 23, 24 is, for example, as shown in fig. 1, passed through the second and third cyclones 23, 24 into the two annular combustion channels 201, 202 of the precombustor 20, respectively. The air b passing through the third cyclone 24 is thoroughly mixed with the spray droplets 6 from the centrifugal nozzle 22. The pre-combustion gas-liquid mixture is further mixed with the air c passing through the second cyclone 23 to achieve the effect of full atomization and evaporation. The pre-combustion stage gas-liquid mixture after being mixed by the air c passes through the second contraction structure 213 and then enters the second expansion structure 214, and then enters the combustion container 200 to form the diffusion combustion pre-combustion stage flame 13. The second expansion structure 214 extends axially to the downstream end of the annular body 21, the second contraction structure 213 extends axially to the upstream end of the second expansion structure 214, and the second expansion structure 214 is provided with a certain expansion angle, so that the precombustion stage flame can be fully expanded and fully contacted with the main combustion stage flame, combustion is more complete, combustion uniformity is improved, and pollution emission is reduced.

"the axial position of the second constriction 213 is located upstream of the first constriction 102 of the main combustion mixer 10", in particular that the first constriction 102 is closer to the combustion vessel 200 (the combustion vessel 200 may be, for example, a flame tube of a combustion chamber of a gas turbine engine as shown in the figures), whereas the second constriction 213 is further from the combustion vessel 200. The principle of this arrangement is that at lower engine thrust, the spray droplets 6 exiting the centrifugal nozzle 22 may need to travel a longer distance to achieve sufficient atomization and evaporation to promote more complete combustion. In the case of high thrust of the engine, the main combustion stage gas-liquid mixture 5 formed by the main combustion mixer 10 needs to be capable of being atomized and evaporated quickly under the action of the high-temperature high-pressure air a to enter the combustion container 200, and as shown in fig. 1, the pre-combustion stage flame 13 can be fully expanded first, so that the mixture of the air and the fuel at the outlet of the main combustion stage can be more uniformly and fully ignited, the combustion uniformity is good, the temperature distribution uniformity of the turbine inlet of the gas turbine engine is improved, and the stable combustion under the condition of high thrust is also facilitated. Thus, the first constriction 102 is closer to the combustion vessel 200 in axial position than the second constriction 213.

In some embodiments, as shown in fig. 1, the air a passing through the first swirler 51, the air c passing through the second swirler 23 and the air b passing through the third swirler 24 have the same rotation direction, so that the fuel and the air sprayed out from the fuel spray holes 3 are fully and uniformly mixed, the combustion is more efficient and sufficient, and the pollution emission is further reduced.

With continued reference to FIG. 1, in one embodiment, a specific structure for a combustor 1000 of a gas turbine engine may include a combustion vessel 200 and a mixer assembly 100 as described above. The mixer assembly 100 is disposed adjacent the combustion vessel 200, with the downstream end of the annular chamber 101 of the mixer assembly 100 being in direct communication with the combustion vessel 200, configured to provide a flow of a mixture of fuel and air to the combustion vessel 200. The adoption of the combustion chamber 1000 comprising the mixer assembly 100 ensures radial staged combustion, can flexibly adjust fuel according to different working conditions, forms flexible, efficient and stable low-pollution combustion by utilizing the annular direct injection technology of the main combustion mixer, and improves the temperature distribution uniformity of the turbine inlet.

In some embodiments, as shown in fig. 1 and 2, under different working conditions, the fuel proportion provided by the centrifugal nozzle 22 and the first fuel pipeline 41 and the second fuel pipeline 42 is adjusted, so that the combustion organization mode of the combustion chamber is flexibly controlled, and low-pollution combustion is formed. Meanwhile, the burnt high-temperature gas 16 has more uniform temperature distribution, and the uniformity of the temperature distribution of the turbine inlet is improved.

In one embodiment, a specific configuration of the gas turbine engine may be to include the combustor 1000 as described above. The gas turbine engine comprising the combustion chamber 1000 can realize flexible adjustment of fuel and air proportions of the combustion chamber under different working conditions, achieve stable, efficient and low-emission combustion, and improve the uniformity of the temperature distribution of the turbine inlet.

Under different working conditions, the combustion organization mode of the combustion chamber 1000 is flexibly adjusted through different fuel distribution of the precombustion stage flame 13 and the directly injected main combustion stage flame 52, so that pollutant emission is reduced, and the method is specifically divided into the following conditions: (1) Typically, at less than 30% thrust conditions of the gas turbine engine, only pre-combustion mixer 20 is operated; (2) At 50% thrust conditions of gas turbine engine, pre-combustion mixer 20 and main combustion mixer 10 are operating simultaneously, where the fuel split ratio of pre-combustion mixer 20 and main combustion mixer 10 is close; (3) At greater than 70% thrust conditions of gas turbine engine, pre-combustion mixer 20 and main combustion mixer 10 are operating simultaneously, where main combustion mixer 10 is dispensing fuel greater than pre-combustion mixer 20.

When the main combustion stage injection fuel is in a high thrust working condition (generally referred to as that the main combustion stage injection fuel accounts for more than 90% of the injection fuel), high-temperature and high-pressure air is quickly mixed with fine liquid drops formed by the opposite jet atomization of the fuel spray holes 3 in the annular chamber 101 of the main combustion mixer 10, so that lean oil is formed for direct combustion, flashback and spontaneous combustion can be effectively prevented, and combustion stability is improved.

In one embodiment, a specific step of a method for atomizing fuel for a gas turbine engine may include providing a primary mixer. The main mixer is arranged to: fuel is injected into the main mixer through a first fuel orifice located at an annular inner wall of the main mixer and a second fuel orifice located at an annular outer wall of the main mixer, wherein the fuel is atomized by collision of a first fuel stream injected by the first fuel orifice with a second fuel stream injected by the second fuel orifice.

By adopting the method for atomizing fuel for the gas turbine engine, the combustion efficiency can be effectively improved, and the pollutant emission can be reduced.

In summary, the gas turbine engine and the mixer assembly, combustor, and method for atomizing fuel described in the above embodiments may include, but are not limited to, one or a combination of the following:

1. through the structure that the first injection direction points to the annular outer wall, the second injection direction points to the annular inner wall, the hedging injection of the main combustion mixer fuel is realized, the annular main combustion grade fuel is easy to atomize and rapidly mix with air after mutually colliding, the advantages of reducing risks of spontaneous combustion, tempering and unstable combustion relative to premixed combustion of direct injection are reserved, meanwhile, the device also has the advantage of uniform mixing of fuel and air, and the device is characterized in that the hedging injection ensures the uniformity of the rapid mixing of the fuel and the air due to the fact that the hedging injection enables the fuel to mutually spray, the uniformity of a combustion temperature field is also ensured, and therefore the uniformity of the temperature distribution of a turbine inlet of a gas turbine engine is improved.

In addition, the structure of the annular chamber enables the main combustion stage flame to be an integral annular flame, so that the defect of uneven temperature distribution caused by flame coupling interference existing in a plurality of independent main combustion stages distributed in an array mode in a comparison scheme is avoided, and the risks of backfire and spontaneous combustion caused by unstable local flow in a local high-temperature area are avoided. .

2. The adoption of the combustion chamber 1000 comprising the mixer assembly 100 ensures radial staged combustion, can flexibly adjust fuel according to different working conditions, forms flexible, efficient and stable low-pollution combustion by utilizing the annular direct injection technology of the main combustion mixer, and improves the temperature distribution uniformity of the turbine inlet.

3. The gas turbine engine comprising the combustion chamber 1000 can realize flexible adjustment of fuel under the non-working condition, achieve stable, efficient and low-emission combustion and improve the uniformity of the temperature distribution of the turbine inlet.

4. By adopting the method for atomizing fuel for the gas turbine engine, the combustion efficiency can be effectively improved, and the pollutant emission can be reduced.

While the application has been described in terms of preferred embodiments, it is not intended to be limiting, but rather to the application, as will occur to those skilled in the art, without departing from the spirit and scope of the application. Therefore, any modification, equivalent variation and modification of the above embodiments according to the technical substance of the present application fall within the protection scope defined by the claims of the present application.

Claims (15)

1. A mixer assembly (100) for a gas turbine engine, comprising:

a main combustion mixer (10), comprising:

an annular inner wall (1);

-an annular outer wall (2) forming an annular chamber (101) around at least part of said annular inner wall (1);

the plurality of fuel spray holes (3) at least comprise a first fuel spray hole (31) and a second fuel spray hole (32), wherein the first fuel spray hole (31) is positioned on the annular inner wall (1), the first fuel spray hole (31) is provided with a first spray direction (D1), the first spray direction (D1) points to the annular outer wall (2), the second fuel spray hole (32) is positioned on the annular outer wall (2), the second fuel spray hole (32) is provided with a second spray direction (D2), and the second spray direction (D2) points to the annular inner wall (1).

2. The mixer assembly (100) of claim 1, wherein an axial position of the first fuel injection hole (31) is the same as an axial position of the second fuel injection hole (32).

3. The mixer assembly (100) according to claim 1 or 2, wherein the first injection direction (D1) is opposite to the second injection direction (D2).

4. The mixer assembly (100) according to claim 1, wherein at least one of the annular inner wall (1), the annular outer wall (2) has a first constriction (102), the flow area of the annular chamber (101) decreasing in the upstream to downstream direction through the first constriction (102).

5. The mixer assembly (100) according to claim 4, wherein downstream of the constriction (102) there is an expansion (103), the flow area of the annular chamber (101) increasing in the upstream to downstream direction through the expansion (103).

6. The mixer assembly (100) of claim 5, wherein the expansion structure (103) extends axially to a downstream end of the annular chamber (101), and the first contraction structure (102) extends axially to an upstream end of the expansion structure (103).

7. The mixer assembly (100) of claim 5, wherein the axial position of the fuel injection orifice (3) is located between the axial positions of the first constriction (102) and the expansion (103).

8. The mixer assembly (100) according to claim 1, wherein the axial position of the fuel injection holes (3) is at an axial distance of 20mm-30mm from the downstream outlet of the annular chamber (101).

9. The mixer assembly (100) according to claim 1, wherein the mixer assembly (100) further comprises a fuel line (4), the fuel line (4) being fluidly connected with the fuel injection orifice (3).

10. The mixer assembly (100) according to claim 1, wherein a first swirler (51) is provided in the annular chamber (101), the axial position of the first swirler (51) being located in an upstream section (1011) of the annular chamber (101), the axial position of the fuel injection holes (3) being located in a downstream section (1012) of the annular chamber (101).

11. The mixer assembly (100) according to any of the claims 1-10, comprising a precombustion mixer (20), at least part of the precombustion mixer (20) being surrounded by the main combustion mixer (10), the precombustion mixer (20) comprising an annular body (21), the annular body (21) having an outer surface (211), the outer surface (211) constituting an annular inner wall (1) of the main combustion mixer (10).

12. The mixer assembly (100) according to claim 11, wherein the annular body (21) has an inner surface (212), the inner surface (212) having a second constriction (213), the axial position of the second constriction (213) being upstream of the first constriction (102) of the main combustion mixer (10).

13. A combustor (1000) for a gas turbine engine, comprising:

a combustion vessel (200); and

the mixer assembly (100) according to any of claims 1-12 disposed adjacent to the combustion vessel (200), a downstream end of the annular chamber (101) of the mixer assembly (100) being in direct communication with the combustion vessel (200) configured to provide a flow of a mixture of fuel and air to the combustion vessel (200).

14. A gas turbine engine, comprising a combustion chamber (1000) according to claim 13.

15. A method for atomizing fuel for a gas turbine engine, comprising:

providing a primary mixer, the primary mixer being arranged to:

fuel is injected into the main mixer through a first fuel orifice located at an annular inner wall of the main mixer and a second fuel orifice located at an annular outer wall of the main mixer, wherein the fuel is atomized by collision of a first fuel stream injected by the first fuel orifice with a second fuel stream injected by the second fuel orifice.