Combustor airflow path

Abstract

To provide an improved system and method for supplying compressed working fluid from an axial staged injector without reducing cooling delivered to a combustion liner.SOLUTION: A combustor for a turbomachine includes a head end, a liner at least partially defining a hot gas path, and a flow sleeve circumferentially surrounding at least a portion of the liner. The flow sleeve is spaced from the liner to form a cooling flow annulus therebetween. The cooling flow annulus is in direct fluid communication with a high pressure plenum, whereby air from the high pressure plenum flows into the cooling flow annulus and from the cooling flow annulus to the head end. The combustor further includes a first combustion zone and a second combustion zone downstream of the first combustion zone along the hot gas path. A plurality of fuel injectors are in fluid communication with the second combustion zone and are not in direct fluid communication with the high pressure plenum.SELECTED DRAWING: Figure 1

Description

Technical Field

[0001] The present disclosure generally relates to combustors for turbomachinery. More particularly, the present disclosure relates to combustors having axially staged fuel injectors and features defining an air flow path for such combustors.

Background Art

[0002] Turbomachinery is utilized in various industries and applications for energy transfer purposes. For example, a gas turbine engine generally includes a compressor section, a combustion section, a turbine section, and an exhaust section. The compressor section gradually increases the pressure of the working fluid flowing into the gas turbine engine and supplies this compressed working fluid to the combustion section. The compressed working fluid and fuel (e.g., natural gas) are mixed within the combustion section and burned within a combustion chamber to generate high-pressure and high-temperature combustion gases. The combustion gases flow from the combustion section to the turbine section, where they expand to produce work. For example, the expansion of the combustion gases in the turbine section can rotate a rotor shaft connected to a generator to generate electricity. The combustion gases are then discharged from the gas turbine via the exhaust section.

[0003] Gas turbines typically burn hydrocarbon fuels and produce emissions such as nitrogen oxides (NOx) and carbon monoxide (CO). Generally, it is desirable to minimize the generation of such emissions. The oxidation of nitrogen molecules in a gas turbine depends on the temperature of the gas located within the combustor and the residence time of the reactants located in the highest temperature region within the combustor. Thus, the amount of NOx generated by the gas turbine can be reduced either by keeping the combustor temperature below the temperature at which NOx is formed or by limiting the residence time of the reactants in the combustor.

[0004] One technique for controlling the temperature of a combustor involves pre-mixing fuel and air to create a lean fuel-air mixture before combustion. This technique may include axial multi-stage fuel injection, in which a first fuel-air mixture is injected into and burned in the first combustion zone or primary combustion zone of the combustor to produce a main stream of high-energy combustion gases, and a second fuel-air mixture is injected and mixed into the main stream of high-energy combustion gases via multiple fuel injectors or axially multi-staged fuel injector assemblies (sometimes called lateline injectors) that are radially oriented and spaced apart at circumferential intervals located downstream of the primary combustion zone. Axial multi-stage injection increases the likelihood of complete combustion of the available fuel and thus reduces undesirable emissions.

[0005] During combustor operation, one or more liners or ducts that form the path of hot gases through the combustion chamber and / or combustor need to be cooled. Cooling of the liners is typically achieved by guiding a cooling medium, such as compressed working fluid from the compressor, through a cooling flow annular section or channel defined between the liner and the flow sleeve and / or impingement sleeve surrounding the liner. As a result, some of the compressed working fluid may be diverted to pass through axially multi-staged injectors, potentially reducing the amount of cooling delivered to the outside of the combustion chamber.

[0006] Therefore, improved systems and methods for supplying compressed working fluid to axially multi-staged injectors without reducing the cooling provided to the combustion liner or duct are considered useful. [Overview of the project]

[0007] The aspects and benefits of the system provided in this disclosure may be in part described below, or may be obvious from this description, or may be learned through the practice of this technology.

[0008] According to one embodiment, a combustor for turbomachinery is provided. The combustor is coupled to the outer casing of the turbomachinery and is in fluid-related communication with a high-pressure plenum within the outer casing. The combustor includes a head end, a liner that at least partially defines a hot gas path, and a flow sleeve that circumferentially surrounds at least a portion of the liner. The flow sleeve is separated from the liner to form a cooling flow annulus between it and the liner. The cooling flow annulus is in direct fluid-related communication with the high-pressure plenum, so that air from the high-pressure plenum flows into the cooling flow annulus and from the cooling flow annulus to the head end. Furthermore, the combustor includes a first combustion zone defined by the liner and a second combustion zone defined by the liner downstream of the first combustion zone in the hot gas path. Multiple fuel injectors are in fluid-related communication with the second combustion zone. The multiple fuel injectors are configured to directly inject a mixture of fuel and air into the second combustion zone. The multiple fuel injectors are not in direct fluid-related communication with the high-pressure plenum.

[0009] According to another embodiment, a turbomachinery is provided. The turbomachinery includes a compressor extending from an intake to a discharge. The discharge of the compressor supplies a flow of high-pressure air directly to a high-pressure plenum defined within the outer casing of the turbomachinery. The turbomachinery further includes a combustor. The combustor includes a head end, a liner that at least partially defines a hot gas path, and a flow sleeve that circumferentially surrounds at least a portion of the liner. The flow sleeve is separated from the liner to form a cooling flow annulus between it and the liner. The cooling flow annulus is in direct fluid-related contact with the high-pressure plenum, so that air from the high-pressure plenum flows into the cooling flow annulus and out of the cooling flow annulus to the head end. Furthermore, the combustor includes a first combustion zone defined by the liner and a second combustion zone defined by the liner downstream of the first combustion zone in the hot gas path. Multiple fuel injectors are in fluid-related contact with the second combustion zone. Multiple fuel injectors are configured to directly inject a mixture of fuel and air into a second combustion zone. The multiple fuel injectors do not have direct fluid contact with the high-pressure plenum. The turbomachinery further includes a turbine downstream of the combustor and an exhaust section downstream of the turbine.

[0010] These features, aspects, and advantages of this assembly, as well as other features, aspects, and advantages, will be better understood by referring to the following description and the appended claims. The appended drawings incorporated herein and constituting part of this specification illustrate embodiments of the art and, together with the description in the specification, are useful in illustrating the principles of the art.

[0011] A full and implementable disclosure of the System, including best modes of manufacture and use of the Assembly, directed to those skilled in the art, is described herein with reference to the accompanying drawings. [Brief explanation of the drawing]

[0012] [Figure 1] This is a schematic diagram of a turbomachinery according to an embodiment of the present disclosure. [Figure 2]This shows a cross-sectional side view of a portion of an exemplary turbomachine, including an exemplary combustor, which may encompass various embodiments of the present disclosure. [Figure 3] This shows a simplified side cross-sectional view of a portion of a combustor according to one or more embodiments of the present disclosure. [Figure 4] The present disclosure shows a perspective view of a portion of a combustor for a turbomachinery according to one or more embodiments. [Figure 5] The images show cross-sectional views of the flanges of combustors for turbomachinery according to one or more embodiments of the present disclosure. [Figure 6] The following are cross-sectional views of the flanges of combustors for turbomachinery according to one or more further embodiments of the present disclosure. [Figure 7] This diagram shows schematic cross-sectional views of a portion of a specific component of a combustor for a turbomachinery according to one or more embodiments of the present disclosure. [Modes for carrying out the invention]

[0013] Hereinafter, embodiments of the System are referred to in detail, with one or more examples shown in the drawings. Each example is presented for illustrative purposes of the Art and is not intended to limit the Art. In fact, it will be apparent to those skilled in the art that modifications and changes are possible in the Art without departing from the scope or spirit of the claimed Art. For example, features illustrated or described as part of one embodiment can be used in another embodiment to bring about further embodiments. Thus, this disclosure is intended to encompass modifications and changes that fall within the scope of the appended claims and their equivalents.

[0014] In the detailed description, numerals and letters are used to refer to features in the drawings. Similar or identical reference numerals in the drawings and description are used to refer to similar or identical parts of the present invention. As used herein, the terms “first,” “second,” and “third” may be used interchangeably to distinguish one component from another and are not intended to indicate the location or importance of any individual component.

[0015] As used herein, the terms “upstream” (or “forward”) and “downstream” (or “backward”) refer to directions relative to the flow of fluid in a fluid path. For example, “upstream” refers to the direction in which the fluid is flowing, and “downstream” refers to the direction in which the fluid is flowing. The term “radial” refers to a relative direction substantially perpendicular to the axial centerline of a particular component, the term “axial” refers to a relative direction substantially parallel and / or coaxial with the axial centerline of a particular component, and the term “circumferential” refers to a relative direction extending around the axial centerline of a particular component. Approximate terms such as “approximately” or “about” include values ​​within plus or minus 10 percent of the stated value. When used in the context of angles or directions, such terms include a range of plus or minus 10 degrees of the stated angle or direction. For example, “approximately perpendicular” includes directions within 10 degrees from perpendicular to any direction, such as clockwise or counterclockwise.

[0016] Referring here to the drawings, Figure 1 shows a schematic diagram of one embodiment of a turbomachinery, which in the illustrated embodiment is a gas turbine 10. Although industrial or onshore gas turbines are shown and described herein, this disclosure is not limited to industrial or onshore gas turbines unless specifically stated in the claims. For example, the systems described herein can be used in any type of turbomachinery, including, but not limited to, steam turbines, aircraft gas turbines, or marine gas turbines.

[0017] As shown in the figure, the gas turbine 10 generally includes an inlet section 12, a compressor section 14 located downstream of the inlet section 12, a combustor section 16 located downstream of the compressor section 14 containing multiple combustors 50 (one example of which is shown in Figure 2), a turbine section 18 located downstream of the combustor section 16, and an exhaust section 20 located downstream of the turbine section 18. In addition, the gas turbine 10 may include one or more shafts 22 connected between the compressor section 14 and the turbine section 18.

[0018] The compressor section 14 may generally include a plurality of rotor disks 24 (one of which is illustrated) and a plurality of rotor blades 26 extending radially outward from each rotor disk 24 and connected to each rotor disk 24. Each rotor disk 24 may then be connected to a portion of a shaft 22 extending through the compressor section 14, or can form such a portion.

[0019] The turbine section 18 may generally include a plurality of rotor disks 28 (one of which is illustrated) and a plurality of rotor blades 30 extending radially outward from each rotor disk 28 and connected to each rotor disk 28. Each rotor disk 28 may then be connected to, or form, a portion of, a shaft 22 extending through the turbine section 18. The turbine section 18 may further include an outer casing 31 that circumferentially surrounds the portion of the shaft 22 and the rotor blades 30, thereby at least partially defining a hot gas path 32 through the turbine section 18.

[0020] During operation, a working fluid such as air flows through the inlet section 12 into the compressor section 14, where the air is gradually compressed, and thus pressurized air is delivered to the combustors of the combustor section 16. The pressurized air is mixed with fuel and burned in each combustor to produce combustion gases 34. The combustion gases 34 flow from the combustor section 16 to the turbine section 18 through the high-temperature gas path 32, where energy (kinetic energy and / or thermal energy) is transferred from the combustion gases 34 to the rotor blades 30, causing the shaft 22 to rotate. This mechanical rotational energy can then be used to operate the compressor section 14 and / or generate electricity. The combustion gases 34 leaving the turbine section 18 can then be discharged from the gas turbine 10 through the exhaust section 20.

[0021] Figure 2 shows a cross-sectional side view of a portion of an exemplary gas turbine 10, including an exemplary combustor 50, which may be one of several combustors provided in the combustor section 16 described above, for example, as shown in Figure 1. The illustrated exemplary combustor 50 can encompass various embodiments of the present disclosure. As shown, the combustor 50 is at least partially enclosed by an outer casing 52 (such as a compressor discharge casing 54 located downstream of the compressor 14) and / or an outer turbine casing 56. The outer casing 52 is in fluid-related contact with the compressor 14 and at least partially defines a high-pressure plenum 58 that surrounds at least a portion of the combustor 50. An end cover 60 is connected to the outer casing 52 at one end of the combustor 50.

[0022] As shown in FIG. 2, the combustor 50 generally includes at least one axially extending fuel nozzle 62 extending downstream from the end cover 60, an annular cap assembly 64 extending radially and axially within the outer casing 52 downstream from the end cover 60, an annular hot gas path duct or combustion liner 66 extending downstream from the cap assembly 64, and an annular flow sleeve 68 surrounding at least a portion of the combustion liner 66. The combustion liner 66 defines a hot gas path 70 for guiding the combustion gas 34 through the combustor 50. The end cover 60 and the cap assembly 64 at least partially define the head end 72 of the combustor 50.

[0023] The cap assembly 64 generally includes a front end portion 74 disposed downstream of the end cover 60, a rear end portion 76 disposed downstream of the front end portion 74, and one or more annular shrouds 78 extending at least partially therebetween. In certain embodiments, the axially extending fuel nozzle 62 extends at least partially through the cap assembly 64 to supply a first combustible mixture 80 primarily composed of fuel and a portion of the compressed working fluid 19 from the compressor 14, such as air, to a primary combustion zone 82 defined within the combustion liner 66 downstream of the rear end portion 76 of the cap assembly 64.

[0024] In certain embodiments, the combustor 50 further includes one or more radially extending fuel injectors 84 (also known as axially staged fuel injectors or downstream lean fuel injectors) extending through the flow sleeve 68 and the combustion liner 66 at a location downstream of at least one axially extending fuel nozzle 62. The combustion liner 66 defines a combustion chamber 86 within the combustor 50. In certain embodiments, the combustion liner 66 further defines a secondary combustion zone 88 located downstream of the primary combustion zone 82 in proximity to the fuel injector 84. In certain embodiments, the combustion liner 66, the flow sleeve 68, and the fuel injector 84 extend axially through the outer casing 52 and are provided as part of a combustion module 100 that circumferentially surrounds at least a portion of the cap assembly 64.

[0025] The combustion module 100 includes a front end or upstream end 102 that is axially spaced from the rear end or downstream end 104 with respect to the axis center line 106 (FIG. 4) of the combustion module 100. As shown in FIG. 2, the combustion liner 66 extends downstream to the rear frame 130 and terminates at the rear frame 130. An attachment bracket 131 can be connected to the rear frame 130. In some embodiments, the rear frame 130 and / or the attachment bracket 131 can be coupled to the outer turbine casing 56 to constrain the combustion module 100 at both the front end 102 and the rear end 104 of the combustion module 100, and the attachment flange 112 can be connected to the compressor discharge casing 54.

[0026] FIG. 3 shows a simplified side cross-sectional view of a portion of the combustor 50 according to various embodiments of the present disclosure. As seen in FIG. 3, the flow sleeve 68 can circumferentially surround at least a portion of the liner 66, and the flow sleeve 68 is spaced from the liner 66 and can form a cooling flow diversion annulus 90 therebetween. The compressed working fluid 19 from the compressor discharge plenum 58 can flow along the outside of the liner 66 through the cooling flow diversion annulus 90 and provide convective cooling to the liner 66 before reversing direction to flow through the head end 72 and the axially extending fuel nozzle 62 (FIG. 2).

[0027] Multiple fuel injectors 84 can be arranged circumferentially around the liner 66 and flow sleeve 68 downstream of the primary fuel nozzle 62. The fuel injectors 84 penetrate the liner 66 and flow sleeve 68, providing fluid communication to the combustion chamber 86. The fuel injectors 84 can receive the same or different fuel as the fuel supplied to the fuel nozzle 62, mix the fuel with a portion of the compressed working fluid 19, or inject the mixture into the combustion chamber 86 while mixing. In this way, the fuel injectors 84 can directly supply the mixture of fuel and compressed working fluid 19 to the secondary combustion zone 88 for additional combustion to increase the temperature and therefore the efficiency of the combustor 50. In exemplary embodiments, the fuel is carried through defined passages within the flow sleeve 68, but instead, fuel conduits located radially outside the flow sleeve 68 (as shown in Figure 4) may be used.

[0028] In some embodiments, as shown in Figure 3, the combustor 50 may include at least one air shield 92 surrounding some or all of the fuel injectors 84. For example, a single air shield 92, as shown in Figure 3, may in some embodiments circumferentially surround the fuel injectors 84, shielding them from direct impact by the compressed working fluid 19 flowing out of the compressor 14. Thus, the fuel injectors 84 are not in direct contact with the high-pressure plenum 58 with respect to the fluid. The air shield 92 may be press-fitted or otherwise connected around the mounting flange 112 and / or the flow sleeve 68 to result in a substantially enclosed volume or a second annular passage 94 between the air shield 92 and the flow sleeve 68. The air shield 92 may extend axially along a portion or the entire length of the flow sleeve 68, ending at the fuel injectors 84, or slightly behind the fuel injectors 84. For example, in a particular embodiment shown in Figure 3, the air shield 92 extends axially along the entire length of the flow sleeve 68 such that the air shield 92 has substantially the same extension as the flow sleeve 68.

[0029] In some embodiments, as shown in Figure 4, for example, there may be one air shield 92 for each fuel injector 84, and multiple air shields 92 may be provided, such as one air shield 92 for each fuel injector 84 in a one-to-one correspondence between the air shields 92 and the fuel injectors 84, so that each fuel injector 84 is surrounded by each air shield 92. As shown in Figure 4, each fuel injector 84 can be connected to a fuel source via a fluid conduit 126 extending between the fuel injector 84 and the mounting flange 112. Also, as seen in Figure 4, the rear frame 130 may be located at the rear or downstream end 128 of the combustion liner 66 and may extend around the rear or downstream end 128. For example, the rear frame 130 may circumferentially surround the rear end 128, as shown in Figure 4.

[0030] Figure 5 shows a cross-sectional view of a flange 112 for use in an embodiment including a single air shield 92, for example, as shown in Figure 3. In such an embodiment, the flange 112 may include a single passage 96 that is continuous around the flange 112, for example, the single passage 96 may extend circumferentially around the entire flange 112, as shown in Figure 5. Figure 6 shows a cross-sectional view of a flange 112 for use in an embodiment including multiple air shields 92, for example, as shown in Figure 4. In such an embodiment, the flange 112 may include multiple passages 96 that pass through the flange 112, and the multiple passages 96 may be arranged in a circumferential array over the entire flange 112, for example, the multiple passages 96 may be spaced apart around the circumference of the flange 112 so that each passage 96 is circumferentially aligned with its respective air shield 92 and fuel injector 84, as shown in Figure 6.

[0031] The air shield 92 or the enclosed volume 94 defined by each air shield 92 can be made directly connected with respect to the fluid to the slots or passages 96 of the flange 112, for example, as shown in Figures 3 and 7, to receive a direct flow of compressed working fluid 19, such as air, from the flange 112, for example, through one or more passages 96 of the mounting flange 112, and to deliver the air 19 to the multiple fuel injectors 84. For example, in various embodiments, a portion of the air 19 flowing through the cooling flow annular section 90 can be directed radially outward to the passages 96, for example, as shown in Figure 7. Furthermore, the airflow 19 from the flange 112 to the multiple fuel injectors 84 may be the sole airflow to the multiple fuel injectors 84. Therefore, the multiple fuel injectors 84 are located entirely downstream of the flange 112 and can only communicate indirectly with respect to fluids with respect to the high-pressure plenum 58 and the cooling flow annular section 90, for example, via the flange 112, and the compressed working fluid (e.g., air) 19 travels through the entire cooling flow annular section 90 and then, only after traveling through at least the flange 112, reaches the multiple fuel injectors 84. Thus, the compressed working fluid can only flow to the multiple fuel injectors 84 after traveling through the entire cooling flow annular section 90, for example, along a continuous and uninterrupted flow path from the high-pressure plenum 58 to the flange 112. For example, the flow path from the high-pressure plenum 58 to the flange 112 does not need to be interrupted in that at least none of the compressed working fluid 19 from the high-pressure plenum 58 goes toward the multiple fuel injectors 84 before reaching the flange 112. Such a flow path can, for example, advantageously provide improved or enhanced cooling of the liner 66 compared to a design in which a portion of the compressed working fluid 19 can flow directly from the high-pressure plenum 58 to the multiple fuel injectors 84 before reaching the cooling flow annular section 90, such as before the compressed working fluid 19 flows through the entire cooling flow annular section 90.

[0032] This specification discloses the present invention, including its best mode, and uses examples to enable those skilled in the art to carry out the invention, including the manufacture and use of any apparatus or system and the execution of any related methods. The patentable scope of the present invention is defined by the claims and may include other embodiments that a person skilled in the art could conceive. Such other embodiments are included in the technical scope of the claims if they include structural elements that do not differ from the language of the claims, or if they include equivalent structural elements that do not differ substantially from the language of the claims. [Explanation of symbols]

[0033] 10 Gas Turbines 12 Entrance Section 14 Compressor Section 16. Combustor Section 18 Turbine Section 19 Working fluid, air 20 Exhaust Section 22 shafts 24 Rotor Discs 26 rotor blades 28 Rotor Discs 30 rotor blades 31 Outer casing 32 High-temperature gas pathway 34 Combustion gases 50 Combustors 52 Outer casing 54 Compressor discharge casing 56. Outer turbine casing 58 High-pressure plenum, compressor discharge plenum 60 End cover 62 Primary fuel nozzle 64 Cap Assembly 66 Combustion Liner 68 Flow Sleeve 70 High-temperature gas pathway 72 Head Ends 74 Front end 76 Rear end 78 Ring Shroud 80 Flammable mixture 82 Primary Combustion Zone 84 Fuel Injector 86 Combustion chamber 88 Secondary combustion zone 90 Cooling flow annular section 92 Air Shield 94 Circular Passage 96 aisle 100 Combustion Modules 102 Front end, upstream end 104 Rear end, downstream end 106 Axis center line 112 Mounting flange 126 Fluid conduit 128 Rear end, downstream end 130 Rear frame 131 Mounting bracket

Claims

1. A turbomachinery assembly comprising a combustor (50), an outer casing (31, 52), and a high-pressure plenum (58), The combustor (50) is coupled to the outer casing (31, 52) and is in fluid communication with the high-pressure plenum (58) within the outer casing (31, 52). The combustion device (50) is Head end (72) and, A flange (112) positioned in close proximity to the head end (72), A liner (66) that at least partially defines a high-temperature gas path (32, 70) including a first combustion zone and a second combustion zone downstream of the first combustion zone, A flow sleeve (68) surrounds at least a portion of the liner (66) circumferentially and is separated from the liner (66) to form a cooling flow annular portion (90) between itself and the liner (66), and the cooling flow annular portion (90) is in direct contact with the high-pressure plenum (58) with respect to the fluid (19), so that air (19) from the high-pressure plenum (58) flows into the cooling flow annular portion (90) and flows from the cooling flow annular portion (90) to the head end (72), Multiple fuel injectors (84) are configured to communicate with the second combustion zone in terms of fluid (19) and to directly inject a mixture of fuel and air (19) supplied through a plurality of fluid conduits (126) into the second combustion zone, A fuel nozzle (62) extends axially and supplies a first combustible mixture (80), which mainly consists of fuel and a portion of the air (19) flowing from the cooling flow annular portion (90) to the head end (72), to the first combustion zone (82), Multiple air shields (92) surrounding a portion of the multiple fuel injectors (84), Multiple volumes (94) enclosed between the multiple air shields (92) and the flow sleeve (68), Equipped with, The plurality of fuel injectors (84) are not in direct contact with the high-pressure plenum (58) with respect to the fluid (19), The plurality of fluid conduits (126) extend between the plurality of fuel injectors (84) and the flange (112) within the plurality of volumes (94), The flange (112) is connected to the outer casing (31, 52), The flange (112) provides for a plurality of passages (96) that are in contact with the fluid (19) in the cooling flow annular portion (90) in order to guide the flow of air (19) from the cooling flow annular portion (90) to the plurality of fuel injectors (84). The plurality of fuel injectors (84) extend radially through the flow sleeve (68) and the liner (66) at a point downstream of the fuel nozzle (62), The plurality of passages (96) of the flange (112) are An inlet for receiving the air (19) from the cooling flow annular portion (90) from the radial direction, An outlet that discharges the air (19) received from the inlets of the plurality of passages (96) axially into the plurality of volumes (94), An assembly comprising:

2. The assembly according to claim 1, wherein the combustor (50) defines a continuous and uninterrupted flow path from the high-pressure plenum (58) through the cooling flow annular section (90) to the head end (72).

3. The assembly according to claim 1, wherein each of the plurality of air shields (92) surrounds a corresponding one of the plurality of fuel injectors (84), and each of the plurality of fuel injectors (84) is surrounded by a corresponding air shield (92) of the plurality of air shields (92).

4. The assembly according to claim 1, wherein the flow of air (19) that is led to the plurality of fuel injectors (84) through the plurality of passages (96) of the flange (112) is the sole flow of air (19) to the plurality of fuel injectors (84).

5. The assembly according to claim 1, wherein the plurality of passages (96) of the flange (112) include four passages (96).

6. It is a turbomachinery, A turbomachinery comprising a compressor (14) extending from an intake to a discharge section and an assembly according to any one of claims 1 to 5, wherein the discharge section of the compressor (14) brings a flow of high-pressure air (19) directly to a high-pressure plenum (58) defined within the outer casing (31, 52) of the turbomachinery.

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