CN211084132U

CN211084132U - Fuel nozzle, combustion chamber, and gas turbine

Info

Publication number: CN211084132U
Application number: CN201921170140.8U
Authority: CN
Inventors: 柴象海; 刘传欣; 王少辉; 翁依柳; 龙丹
Original assignee: AECC Commercial Aircraft Engine Co Ltd
Current assignee: AECC Commercial Aircraft Engine Co Ltd
Priority date: 2019-07-23
Filing date: 2019-07-23
Publication date: 2020-07-24
Anticipated expiration: 2029-07-23

Abstract

The utility model relates to a fuel nozzle, combustion chamber, gas turbine. The fuel nozzle comprises a fuel inlet end, a fuel outlet end and a nozzle body positioned between the fuel inlet end and the fuel outlet end, wherein the fuel inlet end is provided with a fuel inlet, the fuel outlet end is provided with a fuel outlet, the nozzle body comprises an oil inlet cavity, an oil return cavity and a main oil way, and the oil inlet cavity, the oil return cavity and the main oil way respectively extend between the fuel inlet end and the fuel outlet end; the fuel enters the fuel nozzle from a fuel inlet end of the fuel nozzle, sequentially passes through the fuel inlet cavity, the fuel return cavity and the main oil way, and is sprayed out from a fuel outlet end, the fuel return cavity and the fuel inlet cavity are constructed to guide the fuel to flow back, and the fuel return cavity and the main oil way are constructed to guide the fuel to flow back. The fuel nozzle has the advantages of improving the temperature of fuel at the fuel outlet, optimizing the atomization effect of the fuel, improving the combustion efficiency and the like.

Description

Fuel nozzle, combustion chamber, and gas turbine

Technical Field

The utility model relates to a fuel nozzle, combustion chamber, gas turbine.

Background

With the development of high-performance and high-pressure-ratio aircraft engines, the demand for cooling engine devices by using fuel oil as a coolant is rapidly increased, so that the temperature of the fuel oil before entering a fuel oil nozzle is increased to 100-140 ℃; meanwhile, along with the continuous increase of the pressure ratio of the engine to improve the circulation efficiency, the temperature of the inlet air of the combustion chamber is further improved, and the temperature of the inlet air of the combustion chamber of the first-stage engine with the thrust-weight ratio of 10 reaches over 800K, so that the temperature of the wall surface of a main oil way in the fuel nozzle is continuously improved, fuel in the nozzle is seriously deposited and coked and is attached to the inner wall of the main oil way, and a nozzle can be partially blocked when the temperature is serious, a spray cone is blocked, and the quality of oil spraying and atomization is rapidly deteriorated. Poor and unstable atomization quality of fuel oil can cause difficult and irregular ignition flame connection of a combustion chamber and reduction of combustion efficiency, sometimes, unstable and deteriorated temperature distribution of fuel gas at the outlet of the combustion chamber can be caused by unstable fuel oil concentration field, and burning of a flame tube, a turbine guide and rotor blades can be caused in serious cases.

The fuel nozzle is one of the key parts of the combustion chamber of the gas turbine, for example, in the annular combustion chamber, the fuel nozzle is uniformly distributed on the flame tube head positioning device and is fixed on the combustion chamber casing through the bolt of the nozzle mounting plate. The fuel oil enters the nozzle rod core through an external pipeline and enters the flame tube of the combustion chamber for participating in combustion through rotational flow atomization. The fuel nozzle is adjacent to the diffuser outlet, the temperature of the diffuser outlet is about 500-1000K, and the fuel nozzle bears a large heat load under high-temperature airflow, so that in the structure of the existing fuel nozzle, heat insulation measures are taken for a main oil way of the fuel nozzle so as to reduce heat transfer of an external heat source to fuel. For example, CN106556030A entitled "fuel nozzle for combustion chamber and its thermal protection structure", published as 2017, 04/05, discloses a thermal protection structure for a fuel nozzle, which includes a thermal protection tube and a heat exchange structure, the thermal protection tube is used to surround the outside of a main oil path, and the inner wall surface of the thermal protection tube is also used to form a thermal protection space with the outer wall surface of the main oil path, the thermal protection space is divided into an air inlet part and an air outlet part which are separated and located at two sides of the main oil path, the air inlet part and the air outlet part of the thermal protection space are used to form a cooling air flow channel with the inner cavity of the tube wall of the outlet section of the nozzle, wherein the heat exchange structure is arranged in the thermal protection space, the heat exchange structure includes a plurality of transverse ribs and a plurality of longitudinal ribs, the plurality of transverse ribs are arranged perpendicular to the flow direction of cooling air, the plurality of longitudinal rib plates are arranged to be radially distributed by taking the oil inlet pipe as a center and are respectively intersected with the plurality of transverse rib plates, and the transverse rib plates are provided with a plurality of airflow holes for cooling air to flow.

The inventor finds that the fuel in the main oil way can be cooled excessively due to the arrangement of the cooling structure, so that the temperature sprayed from the fuel outlet of the fuel nozzle is insufficient, the fuel atomization effect is influenced, and the combustion efficiency is reduced.

Therefore, there is a need in the art for a fuel nozzle, a combustion chamber, and a gas turbine, which can increase the temperature of the fuel at the fuel outlet to improve the atomization effect of the fuel, improve the combustion efficiency of the combustion chamber, reduce the fuel consumption of the gas turbine, and ensure the stability and safety of the combustion in the combustion chamber and the operation of the gas turbine.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide a fuel nozzle.

Another object of the present invention is to provide a combustion chamber.

It is yet another object of the present invention to provide a gas turbine.

According to the utility model discloses a fuel nozzle of an aspect, including fuel entrance point, fuel exit end and the nozzle body that is located between fuel entrance point, fuel exit end, the fuel entrance point has the fuel import, the fuel exit end has the fuel export, the nozzle body includes oil feed chamber, returns oil chamber and main oil circuit, oil feed chamber, returns oil chamber and main oil circuit extend respectively between fuel entrance point, fuel exit end; the fuel enters the fuel nozzle from a fuel inlet end of the fuel nozzle, sequentially passes through the fuel inlet cavity, the fuel return cavity and the main oil way, and is sprayed out from a fuel outlet end, the fuel return cavity and the fuel inlet cavity are constructed to guide the fuel to flow back, and the fuel return cavity and the main oil way are constructed to guide the fuel to flow back.

In one or more embodiments of the fuel nozzle, the return chamber interior space is configured to direct fuel to flow back.

In one or more embodiments of the fuel nozzle, the oil return cavity is located at the periphery of the main oil path, and the oil inlet cavity is located at the periphery of the oil return cavity.

In one or more embodiments of the fuel injector, the main oil passage includes a central chamber, the oil return cavity includes a first peripheral chamber peripherally adjacent around the main oil passage, and the oil inlet cavity includes a second peripheral chamber peripherally adjacent around the oil return cavity.

In one or more embodiments of the fuel nozzle, an axis of the central chamber coincides with an axis of the nozzle body, and the central chamber, the first peripheral chamber, and the second peripheral chamber are concentrically arranged.

In one or more embodiments of the fuel injector, a first divider is disposed within the first peripheral chamber dividing the first peripheral chamber into a plurality of separate first peripheral subchambers; the fuel nozzle is characterized in that a second partition is arranged in the second peripheral cavity and divides the second peripheral cavity into a plurality of independent second peripheral sub-cavities, each of the plurality of first peripheral sub-cavities corresponds to one second peripheral sub-cavity arranged at the periphery, each of the plurality of second peripheral sub-cavities corresponds to one fuel inlet, so that fuel enters the fuel nozzle from a plurality of fuel inlet ends, sequentially passes through the plurality of second peripheral sub-cavities and the plurality of first peripheral sub-cavities and then is collected into the central cavity, and then is sprayed out from the fuel outlet end of the fuel nozzle

In one or more embodiments of the fuel nozzle, an annular housing is disposed around the fuel outlet end, and the annular housing and an outer sidewall of the outlet end form an insulating cavity, so that air in the insulating cavity insulates the periphery of the fuel outlet end.

In one or more embodiments of the fuel nozzle, the outer wall of the oil inlet chamber is an outer wall of the nozzle body that includes a coated region coated with a thermal barrier coating, and the outer wall of the nozzle body is provided with a mounting flange for connection with a combustor casing of a gas turbine such that the fuel nozzle is secured to a combustor.

In one or more embodiments of the fuel nozzle, the fuel nozzle is machined by additive manufacturing.

According to the utility model discloses another aspect's a combustion chamber, including above arbitrary item the fuel nozzle, the fuel nozzle is adjacent with the diffuser export of combustion chamber, follows the air part that the diffuser export flows passes through the outer wall of nozzle body.

According to another aspect of the present invention, a gas turbine includes the above combustion chamber.

The utility model discloses an advance effect includes following one or combination:

1. through the structural design that the oil inlet cavity, the oil return cavity and the main oil way are turned back to flow, the fuel oil in the main oil way is uniformly heated in advance by utilizing the external high temperature of the fuel nozzle, the fuel oil temperature at a fuel oil outlet is improved, the fuel oil atomization effect is optimized, and the combustion efficiency is improved.

2. The outer wall of the nozzle body is coated with a thermal barrier coating to prevent fuel coking caused by overhigh temperature at the periphery of the nozzle.

3. The periphery of the outlet end of the nozzle is provided with an annular shell to form a heat insulation cavity, so that the fuel outlet end is prevented from generating fuel coking in the high-temperature environment of the flame tube.

Drawings

The above and other features, nature and advantages of the present invention will become more apparent from the following description of the embodiments taken in conjunction with the accompanying drawings in which like reference characters refer to like features throughout, it being noted that the drawings are given by way of example only and are not to scale, and should not be taken as limiting the scope of the invention which is actually claimed, in which:

FIG. 1 is a schematic illustration of a combustor of a gas turbine in accordance with one or more embodiments;

FIG. 2 is a cross-sectional structural schematic view of a fuel injector according to one or more embodiments;

fig. 3 is a schematic sectional view according to the direction a-a of fig. 2.

Detailed Description

The present invention will be further described with reference to the following embodiments and drawings, and more details will be set forth in the following description in order to provide a thorough understanding of the present invention, but it is obvious that the present invention can be implemented in various other ways different from those described herein, and those skilled in the art can make similar generalizations and deductions according to the actual application without departing from the spirit of the present invention, and therefore, the scope of the present invention should not be limited by the contents of the embodiments.

The following discloses many different embodiments or examples for implementing the subject technology described. Specific examples of components and arrangements are described below to simplify the present disclosure, but these are merely examples and are not intended to limit the scope of the present invention. For example, if a first feature is formed over or on a second feature described later in the specification, this may include embodiments in which the first and second features are formed in direct contact, and may also include embodiments in which additional features are formed between the first and second features, such that the first and second features may not be in direct contact. Additionally, reference numerals and/or letters may be repeated among the various examples throughout this disclosure. This repetition is for the purpose of simplicity and clarity and does not in itself dictate a relationship between the various embodiments and/or configurations discussed. Further, when a first element is described as being coupled or coupled to a second element, the description includes embodiments in which the first and second elements are directly coupled or coupled to each other, as well as embodiments in which one or more additional intervening elements are added to indirectly couple or couple the first and second elements to each other.

Further, it is to be understood that the terms of orientation or positional relationship, such as "front, back, up, down, left, right", "lateral, vertical, horizontal" and "top, bottom", etc., are generally used in the sense of being based on the orientation or positional relationship shown in the drawings, and are used for convenience in describing and simplifying the present invention, and in the case of not being described to the contrary, these terms of orientation do not indicate and imply that the device or element so referred to must have a particular orientation or be constructed and operated in a particular orientation, and therefore should not be considered as limiting the scope of the present invention. Also, this application uses specific language to describe embodiments of the application. The terms "inside" and "outside" refer to the inside and the outside of the outline of each component itself, and the terms "first" and "second" are used to define the components, so as to distinguish the corresponding components only, and if not stated otherwise, the terms have no special meaning, and therefore, the scope of the present invention should not be construed as being limited. Reference throughout this specification to "one embodiment," "an embodiment," and/or "some embodiments" means that a particular feature, structure, or characteristic described in connection with at least one embodiment of the present application is included in at least one embodiment of the present application. Therefore, it is emphasized and should be appreciated that two or more references to "an embodiment" or "one embodiment" or "an alternative embodiment" in various places throughout this specification are not necessarily all referring to the same embodiment. Furthermore, some features, structures, or characteristics of one or more embodiments of the present application may be combined as appropriate.

As shown in fig. 1, the gas turbine is exemplified by a turbofan engine. The device comprises a fuel nozzle 1, a combustion chamber outer casing 2, a combustion chamber inner casing 3, a combustion chamber inlet 4 and a flame tube 5; the central staged combustion chamber is taken as an example in the combustion chamber of the turbofan engine and comprises a pre-combustion stage and a main combustion stage surrounding the pre-combustion stage, the fuel nozzle 1 is a pre-combustion stage nozzle, air is reserved from an inlet of the combustion chamber, namely an outlet of a diffuser, a flame tube 5 entering the combustion chamber is mixed with fuel sprayed from the fuel nozzle 1 to generate combustion reaction, the temperature of the air flowing out from the outlet of the diffuser can reach over 800K, and at least a part of the flowing air passes through the outer wall of a nozzle body of the fuel nozzle 1 and transfers the heat of high-temperature air to the nozzle body.

Referring to fig. 2 and 3, in one or more embodiments, the specific structure of the fuel nozzle 1 includes a fuel inlet end 10, a fuel outlet end 16, and a nozzle body 18 located between the fuel inlet end 10 and the fuel outlet end 16, where the fuel inlet end 10 has a fuel inlet 11, the fuel outlet end 16 has a fuel outlet 15, the nozzle body 18 includes an oil inlet chamber 12, an oil return chamber 13, and a main oil path 14, and the oil inlet chamber 12, the oil return chamber 13, and the main oil path 14 extend between the fuel inlet end 10 and the fuel outlet end 16, respectively; as shown by arrows in fig. 2, the oil inlet chamber 12, the oil return chamber 13 and the main oil path 14 are configured such that fuel enters the fuel nozzle from the fuel inlet end 10 of the fuel nozzle 1, passes through the oil inlet chamber 12, the oil return chamber 13 and the main oil path 14 in sequence, and is finally ejected from the fuel outlet end 16, the oil return chamber 13 and the oil inlet chamber 12 are configured to guide fuel to flow back, and the oil return chamber 13 and the main oil path 14 are configured to guide fuel to flow back. The beneficial effect that so sets up lies in, can utilize the fuel flow effect between oil feed chamber 12, oil return chamber 13 and the main oil way 14, evenly transmits the nozzle body to the fuel of main oil way 14 with the heat of air in, plays the effect of preheating to the fuel of main oil way 14, improves fuel outlet fuel temperature, optimizes the atomizing effect of fuel, improves the combustion efficiency of combustion chamber, has also promoted gas turbine's fuel economy. Meanwhile, as the fuel oil fully flows among the oil inlet cavity 12, the oil return cavity 13 and the main oil way 14, the heat is uniformly transferred, the condition of local fuel oil coking is also reduced, and the combustion stability of the combustion chamber and the safety and reliability of the operation of the gas turbine are ensured. It can be understood that the structure of the oil return cavity 13 is not limited to that shown in fig. 2 and 3, and the inside of the oil return cavity 13 may also be configured to be a structure for guiding the fuel oil to flow back, taking the structure of the oil return cavity 13 in fig. 2 to 3 as an example, only one pipe wall is arranged between the oil inlet cavity 12 and the main oil way 14, and the fuel oil flows along a single linear path in the oil return cavity 13, or multiple pipe walls with a certain distance may be arranged, so that the fuel oil flows along multiple parallel linear paths in the oil return cavity 13, and thus the heat distribution may be more uniform, but certain processing difficulty may be increased.

With continued reference to fig. 2 and 3, in one or more embodiments, the fuel injector 1 may be configured such that the return chamber 13 is located at the periphery of the main oil path 14, and the oil inlet chamber 12 is located at the periphery of the return chamber 13. Therefore, the heat exchange area of the convection heat transfer is increased, the heat distribution is further more uniform, and the heating efficiency of the fuel oil of the main oil way 14 is improved. The specific structure may be that the main oil passage 14 includes a central cavity 140, the oil return cavity 13 includes a first peripheral cavity 130 peripherally adjacent to and surrounding the main oil passage 14, and the oil inlet cavity 12 includes a second peripheral cavity 120 peripherally adjacent to and surrounding the oil return cavity 13. Further, the relative positional relationship of the central chamber 140, the first peripheral chamber 130, and the second peripheral chamber 120 may be such that the axis of the central chamber 140 coincides with the axis of the nozzle body 18, and the central chamber 140, the first peripheral chamber 130, and the second peripheral chamber 120 are concentrically disposed. The concentric arrangement has the advantages that the nozzle can be conveniently machined, and the heat and fuel pressure are distributed uniformly. It will be appreciated that the three may be arranged non-concentrically, for example, the axis of the main oil passage 14 is not coincident with the axis of the nozzle body 18, i.e. the main oil passage 14 is arranged eccentrically, and is not limited to the concentric arrangement described above, according to the specific practical requirements. Similarly, the diameters of the oil inlet chamber 12, the oil return chamber 13, and the main oil passage 14 may be changed according to the requirements of the oil supply pressure, the outlet pressure, and the like, and are not limited to the dimensions shown in fig. 2 and 3.

With continued reference to fig. 2 and 3, in one or more embodiments, the first peripheral chamber 130 and the second peripheral chamber 120 may be specifically configured such that a first partition 131 is disposed within the first peripheral chamber 130 to divide the first peripheral chamber 130 into two first

peripheral subchambers

1301, 1302; the second peripheral chamber 120 is internally provided with a second partition 121 which divides the second peripheral chamber 120 into two independent second

peripheral sub-chambers

1201 and 1202, each of the two first

peripheral sub-chambers

1301 and 1302 is provided with one second peripheral sub-chamber corresponding to the periphery, that is, the first peripheral sub-chamber 1301 is provided with the second peripheral sub-chamber 1201 at the periphery, the first peripheral sub-chamber 1303 is provided with the second peripheral sub-chamber 1202 at the periphery, and each of the two second

peripheral sub-chambers

1201 and 1202 corresponds to one fuel inlet port 11, so that fuel enters the fuel nozzle 1 from a plurality of fuel inlet ports 11, sequentially passes through the plurality of second peripheral sub-chambers and the plurality of first peripheral sub-chambers, then is collected into the central chamber 140, and then is sprayed out from the fuel outlet port 15 of the fuel nozzle. The beneficial effect that so sets up lies in, the setting of spacing body can increase structural rigidity for the fuel nozzle keeps longer life under the vibration effect of the air current that receives the pressure of burning reaction in the flame tube and diffuser export, simultaneously, also can make the flow of fuel in the fuel nozzle more smooth and easy, and the heat in the nozzle distributes evenly. It is understood that the number of the first partition 131 and the second partition 121 and the specific number of the first peripheral sub-chamber and the second peripheral sub-chamber may be determined according to specific requirements, and not limited to two first peripheral sub-chambers and two second peripheral sub-chambers as shown in fig. 3, for example, three or more sub-chambers may be provided.

With continued reference to FIG. 2, in one or more embodiments, the specific configuration of the fuel injector 1 may also be such that an annular housing 19 is disposed about the fuel outlet end 16, the annular housing 19 and the outer sidewall of the outlet end 16 defining an insulating cavity 17 such that air within the insulating cavity insulates the fuel outlet end periphery. The fuel nozzle has the advantages that the outlet end 16 of the fuel nozzle is close to the flame tube and is easily influenced by high temperature of combustion in the flame tube, and the heat insulation cavity 17 is arranged to prevent fuel coking from locally occurring at the outlet end 16.

With continued reference to FIG. 2, the particular configuration of the nozzle body 18 may be such that the outer wall of the oil inlet chamber 12 is the outer wall of the nozzle body 18, which includes a coated region 180 coated with a thermal barrier coating, and the outer wall of the nozzle body 18 is provided with a mounting flange 16, the mounting flange 16 being for attachment to the combustor outer case 2 of a gas turbine engine such that the fuel nozzle 1 is secured to the combustor. The beneficial effect of applying a thermal barrier coating is to prevent coking of the fuel due to local overheating. Preferably, the thermal barrier coating may be selected to be a ceramic matrix composite, but not limited thereto.

The fuel nozzle structure introduced in the above embodiment can be processed by an additive manufacturing process, and has the beneficial effects that the fuel nozzle structure can be integrally formed, so that the inlet end and the outlet end of the nozzle, the oil inlet cavity 12, the oil return cavity 13 and the main oil way 14 do not need subsequent assembly processes, and the additive manufacturing method can be specifically realized by using metal powder as a raw material, performing growth manufacturing through laser melting/rapid solidification layer-by-layer deposition, and completing a high-performance structural member by a part CAD model in one step. The heat insulation cavity 17 can also be manufactured by an additive manufacturing method, specifically, a fabrication hole is arranged to take out powder, and the fabrication hole is plugged after molding. The inner cavity surfaces of the oil inlet cavity 12, the oil return cavity 13, the main oil way 14 and other structures can be specifically processed by abrasive flow, so that the surface quality of a flow path of a fuel nozzle is improved, and the flowing characteristic of fuel is improved. And the subsequent heat treatment process can adopt a Hot Isostatic Pressing (HIP) heat treatment process to improve the comprehensive mechanical property of the fuel nozzle. It is understood that other additive manufacturing and subsequent surface treatment and heat treatment processes may be used by one skilled in the art, and are not limited to the above-described processes.

In summary, the advantages of the fuel nozzle, the combustion chamber and the gas turbine are as follows:

Although particular embodiments of the present invention have been described above, it will be appreciated by those skilled in the art that these are examples only and that the scope of the present invention is defined by the appended claims. Various changes and modifications to these embodiments may be made by those skilled in the art without departing from the spirit and scope of the invention, and these changes and modifications are all within the scope of the invention.

Claims

1. A fuel nozzle comprises a fuel inlet end, a fuel outlet end and a nozzle body positioned between the fuel inlet end and the fuel outlet end, wherein the fuel inlet end is provided with a fuel inlet, and the fuel outlet end is provided with a fuel outlet;

the fuel enters the fuel nozzle from a fuel inlet end of the fuel nozzle, sequentially passes through the fuel inlet cavity, the fuel return cavity and the main oil way, and is sprayed out from a fuel outlet end, the fuel return cavity and the fuel inlet cavity are constructed to guide the fuel to flow back, and the fuel return cavity and the main oil way are constructed to guide the fuel to flow back.

2. The fuel injector of claim 1, wherein said return chamber interior volume is configured to direct fuel into a reentrant flow.

3. The fuel injector of claim 1, wherein said return chamber is located about a periphery of said main fuel passage and said inlet chamber is located about a periphery of said return chamber.

4. The fuel injector of claim 3, wherein said main fuel passage includes a central chamber, said return fuel chamber includes a first peripheral chamber peripherally adjacent around said main fuel passage, and said fuel inlet chamber includes a second peripheral chamber peripherally adjacent around said return fuel chamber.

5. The fuel injector of claim 4, wherein an axis of the central chamber coincides with an axis of the injector body, and wherein the central chamber, the first peripheral chamber, and the second peripheral chamber are concentrically disposed.

6. The fuel injector of claim 4, wherein a first partition is disposed within said first peripheral chamber dividing said first peripheral chamber into a plurality of separate first peripheral subchambers; the fuel nozzle is characterized in that a second partition is arranged in the second peripheral cavity and divides the second peripheral cavity into a plurality of independent second peripheral sub-cavities, each of the plurality of first peripheral sub-cavities corresponds to one second peripheral sub-cavity arranged on the periphery, and each of the plurality of second peripheral sub-cavities corresponds to one fuel inlet, so that fuel enters the fuel nozzle from a plurality of fuel inlet ends, sequentially passes through the plurality of second peripheral sub-cavities and the plurality of first peripheral sub-cavities and then is collected into the central cavity, and then is sprayed out from a fuel outlet end of the fuel nozzle.

7. The fuel injector of claim 1, wherein an annular housing is disposed about the fuel outlet end, the annular housing and an outer sidewall of the outlet end defining an insulating cavity such that air within the insulating cavity insulates the fuel outlet end periphery.

8. The fuel injector of claim 1, wherein the outer wall of the oil intake chamber is an outer wall of the injector body that includes a coated region coated with a thermal barrier coating, and the outer wall of the injector body is provided with a mounting flange for coupling with a combustor case of a gas turbine engine such that the fuel injector is secured to a combustor.

9. A fuel injector as claimed in any one of claims 1 to 8, characterized in that the fuel injector is manufactured by additive manufacturing.

10. A combustion chamber comprising a fuel nozzle as claimed in any one of claims 1 to 9 adjacent a diffuser outlet of the combustion chamber, the portion of air flowing from the diffuser outlet passing through an outer wall of the nozzle body.

11. A gas turbine comprising the combustor of claim 10.