JP6804755B2 - Swirl type injection nozzle - Google Patents

Description

The present invention relates to a spiral injection nozzle that injects a fluid in a spiral shape, which is used, for example, as a fuel injection nozzle of a gas turbine engine.

The spiral injection nozzle is a nozzle that granulates fluids such as fuel and water, and is used in various industries including gas turbines. The spiral injection nozzle has a complicated structure, and is assembled by processing a large number of parts individually and then joining the parts by welding, brazing, or the like.

JP-A-2015-117626

However, in such a configuration, an error is likely to occur during assembly, labor is required for assembly, and fluid is likely to leak from the joint. In addition, Patent Document 1 discloses a method of manufacturing an integrated turbine blade without a joint by using a three-dimensional laminated molding technique, which is not a nozzle.

An object of the present invention is to provide a spiral injection nozzle which has high dimensional accuracy, is easy to manufacture, and can prevent fluid leakage.

Hereinafter, for the sake of ease of understanding, reference numerals will be given to the embodiments for convenience.
The spiral injection nozzles of the present invention are spiral injection nozzles 10 and 12 that inject fluid in a spiral shape through a fluid passage 24.
The fluid passage 24 includes swirl passages 30 and 44 that eject the fluid while swirling around the nozzle axes C1 and C2, annular passages 28 and 40 that supply the fluid to the swirl passage, and nozzle axis directions C1. The annular passages 28 and 40 extending to C2 are provided with supply passages 26 and 38 for supplying the fluid.
At least, the heads 20 and 45 including the swivel passages 30 and 44, the annular passages 28 and 40, and the downstream portion of the supply passages 26 and 38 are integrated by three-dimensional modeling.

According to the spiral injection nozzle of the present invention, the heads 20 and 45 having a complicated structure because the swirl passages 30 and 44, the annular passages 28 and 40, and the downstream portions of the supply passages 26 and 38 are included. Since it is composed of an integral body by three-dimensional modeling (3D printer), the dimensional accuracy of the spiral injection nozzles 10 and 12 is high, and the manufacturing becomes easy. Moreover, since the number of joints is reduced, it is possible to prevent fluid leakage.

In the present invention, preferably, the passage cross section of the annular passage 28 is curved at least in the portion 28b facing the nozzle top surface 20a. According to this configuration, even if the metal layers 51 are overlapped when forming the curved portion by the 3D printer, the upper metal layer 51 is sufficiently supported by the lower metal layer 51, so that the fall is avoided, and as a result, the metal layer 51 is prevented from falling. , No need for metal layer support. This makes it possible to easily form the head 20 of the fuel injection nozzle 10 using a 3D printer.

In the present invention, it is preferable that the cross section of the annular passage 28 is circular or elliptical except for the nozzle radial inner portion 28a connected to the swivel passage 30. The circular or oval shape allows the curved portion of the annular passage 28 to be easily formed. Further, the passage resistance of the fluid flowing through the annular passage 28 is smaller than that in the case of the rectangular cross section.

When the spiral injection nozzle of the present invention is used as a fuel injection nozzle of a gas turbine engine,
The fluid passage 24 is a main fuel passage formed at a position eccentric from the nozzle axis C1 and extending in the axial direction.
In addition, it has a primary fuel passage 22
The primary fuel passage 22 communicates with a primary supply passage 32 formed inside the main supply passage 26 in the radial direction of the engine and extending in the nozzle axis C1 direction, and a downstream end portion of the primary supply passage 32. It has a primary annular passage 34 extending inward in the nozzle radial direction and a primary injection chamber 36 communicating with the downstream end of the primary annular passage 34.
The swivel passage 30 and the primary injection chamber 36 may be configured to face the fuel injection port 10a formed on the nozzle top surface 20a.

According to this configuration, a spiral fuel injection nozzle 10 for a gas turbine engine having a main fuel passage 24 and a primary fuel passage 22 can be easily manufactured by a 3D printer.

In the spiral fuel injection nozzle 10 for the gas turbine engine, the swirl passage 30 of the main fuel passage 24 is located outside the nozzle radial direction of the primary injection chamber 36 of the primary fuel passage 22, and the annular passage 28. The nozzle has a plurality of inclined holes 30a extending inward in the radial direction from the inside of the nozzle, and a conical cylindrical inclined chamber 30b communicating with the downstream portion thereof.
The plurality of inclined holes 30a are arranged apart from each other in the circumferential direction of the nozzle axis C1.
The downstream end of the inclined chamber 30b may be configured to communicate with the fuel injection port 10a.

According to this configuration, the main fuel passage 24 and the primary fuel passage 22 can be arranged in the radial direction of the injection nozzle and arranged compactly.

According to the spiral injection nozzle of the present invention, since the head of the spiral injection nozzle having a complicated structure is made of an integral body by three-dimensional modeling, the dimensional accuracy is high and the production is easy. Moreover, since the number of joints is reduced, it is possible to prevent fluid leakage.

It is a vertical cross-sectional view which shows the combustor provided with the spiral type injection nozzle which concerns on one Embodiment of this invention. It is a vertical cross-sectional view which shows the head of the spiral type injection nozzle. It is sectional drawing along the line III-III of FIG. It is a vertical sectional view which shows the head of another example of the same spiral type injection nozzle. It is sectional drawing along the VV line of FIG. It is another vertical sectional view of the main part which shows the manufacturing method of the spiral type injection nozzle. It is a vertical sectional view of the main part which shows the conventional manufacturing method.

Hereinafter, preferred embodiments of the present invention will be described with reference to the drawings. FIG. 1 is a vertical cross-sectional view showing a fuel injection nozzle 10, which is a type of spiral injection nozzle according to the first embodiment of the present invention. The fuel injection nozzle 10 is a double-type spiral injection nozzle that injects fuel in a spiral shape, and is provided in the annular combustor 1 for a gas turbine engine in this embodiment. In the following description, "upstream" and "downstream" refer to upstream and downstream in the fuel flow direction.

The combustor 1 has an annular outer casing 3 and an annular inner casing 4 arranged inside the annular outer casing 3, and both casings 3 and 4 have an annular internal space concentric with the engine rotation axis C. The combustor housing 2 is configured. In the annular internal space of the combustor housing 2, a combustion cylinder 5 in which the annular inner liner 7 is concentrically arranged inside the annular outer liner 6 is arranged concentrically with the combustor housing 2.

A tubular support member 15 is connected to the upstream end of the combustion cylinder 5 by welding. The central axis of the support member 15 coincides with the nozzle axis C1 of the fuel injection nozzle 10. The tip wall 15a of the support member 15 is provided at the downstream end, and an opening 15b facing the axial direction is formed in the tip wall 15a. A first flange portion 15c is formed at the downstream end portion of the support member 15, and a swirl 16 is mounted on the first flange portion 15c. The upstream end of the combustion cylinder 5 is connected to the outside of the swirl 16 by welding. The downstream end of the combustion cylinder 5 communicates with the first stage nozzle (not shown) of the turbine.

A second flange portion 15d is formed at the upstream end of the support member 15, and the support member 15 and the combustor housing 2 are bolted to each other via the second flange portion 15d. A plurality of air intake holes 15e composed of radial through holes are formed in the axially intermediate portion of the peripheral wall 15f of the support member 15.

An annular combustion chamber 8 is formed inside the combustion cylinder 5, and a plurality of fuel injection nozzles 10 for injecting fuel into the combustion chamber 8 are provided at the upstream end of the combustion chamber 5. The fuel injection nozzles 10 are arranged at equal intervals on a single circle concentric with the combustion cylinder 5. Specifically, the fuel injection nozzle 10 is arranged so that the downstream portion including the head portion 20 described later is housed inside the support member 15 and the fuel injection port 10a faces the opening 15b of the support member 15. .. The fuel injection nozzle 10 is supported by the combustor housing 2 by a fastening member (not shown) such as a bolt. An annular nozzle air passage 17 is formed between the peripheral wall 15f of the support member 15 and the peripheral wall 10b of the fuel injection nozzle 10. Details of the structure of the fuel injection nozzle 10 will be described later.

An auxiliary fuel injection nozzle 12 that injects fuel into the combustion chamber 8 is provided so as to penetrate the outer casing 3 and the outer liner 6. The auxiliary fuel injection nozzle 12 is a single type spiral injection nozzle that injects fuel in a spiral shape. The auxiliary fuel injection nozzle 12 injects the auxiliary fuel F0 into the fuel F injected from the fuel injection nozzle 10, and is provided for, for example, for ignition or flame holding. However, the auxiliary fuel injection nozzle 12 may not be provided. The auxiliary fuel injection nozzle 12 is arranged so as to face the radial direction of the combustion cylinder 5 and its axis C2 is orthogonal to the nozzle axis C1 of the fuel injection nozzle 10. Details of the structure of the auxiliary fuel injection nozzle 12 will be described later. An ignition plug 14 for ignition is provided so as to penetrate the outer casing 3 and the outer liner 6.

In the annular internal space between the combustor housing 2 and the combustion cylinder 5, an air passage 25 into which compressed air CA supplied from a compressor (not shown) is introduced is formed. The compressed air CA is supplied into the combustion chamber 8 from a plurality of air introduction ports 18 formed in the swirler 16 of the support member 15 and the outer liners 6 and inner liners 7 of the combustion cylinder 5, respectively, while taking in the air of the support member 15. It is supplied from the hole 15e to the nozzle air passage 17.

The fuel injection nozzle 10 has a primary passage 22 to which the primary fuel F1 is supplied and a main fuel passage 24 to which the main fuel F2 is supplied. The primary fuel F1 is supplied only at start-up and low power, or over the entire power region, and the main fuel F2 is supplied at intermediate power and high power. The primary passage 22 is formed inside the main fuel passage 24 in the engine radial direction. Each of the fuels F0 to F2 is a fluid such as a petroleum-based liquid or natural gas.

As shown in FIG. 2, one der Rume in fuel passage 24 of the fluid passageway, the main supply passage 26 extending in the direction of the nozzle axis C1 is formed at a position eccentric from the nozzle axis C1, the main supply passage It has a main annular passage 28 communicating with the downstream end of the 26, and a plurality of main turning passages 30 extending diagonally downstream from the main annular passage 28 toward the nozzle axis C1. As shown in FIG. 3, the main swivel passage 30 is a type of fluid injection port opened to the nozzle top surface 20a, which is the tip surface of the head portion 20 of FIG. 2, while swirling the main fuel F2 around the nozzle axis C1. The fuel is injected from the fuel injection port 10a.

The cross section of the main annular passage 28 is a circular or elliptical portion in which the portion connected to the main swivel passage 30, that is, the inner side 28a in the nozzle radial direction near the nozzle axis C1 is linear. As shown in FIG. 3, the main swivel passage 30 has a plurality of inclined holes 30a provided so as to be inclined with respect to the radial direction of the nozzle axis C1 when viewed from the direction of the nozzle axis C1, and downstream thereof. It has a conical tubular inclined chamber 30b, and the downstream end of the inclined chamber 30b communicates with the fuel injection port 10a. The fuel injection nozzle 10 is entirely formed of an integral body by three-dimensional modeling (3D printer). However, only the head 20 including the downstream portion of the main supply passage 26 in FIG. 2, the main annular passage 28, and the main swivel passage 30 is made of an integral body by three-dimensional modeling, and the body portion 21 excluding the head 20 is machined. , And both 20 and 21 may be brazed.

The primary fuel passage 22 is formed inside the main supply passage 26 in the engine radial direction at a position eccentric from the nozzle axis C1, and extends in the nozzle axis C1 direction, and a downstream end portion of the primary supply passage 32. A primary annular passage 34 extending inward in the radial direction of the nozzle, an introduction passage 35 extending inward in the radial direction from the primary annular passage 34 toward the nozzle axis C1, and a shaft communicating with the downstream end of the introduction passage 35. It has a primary injection chamber 36 extending in the direction. The primary injection chamber 36 is located on the nozzle axis C1. In the introduction passage 35, a plurality of guide bodies extending in the radial direction of the nozzle axis C1 or in a direction oblique to the radial direction are provided side by side at equal intervals in the circumferential direction of the nozzle axis C1.

The primary annular passage 34 is arranged inside the nozzle axis C1 of the main annular passage 28 in the radial direction. The primary injection chamber 36 is arranged inside the nozzle axis C1 of the main annular passage 28 and the main swivel passage 30 in the radial direction. The outlet of the main swivel passage 30 of the main fuel passage 24 and the outlet of the primary injection chamber 36 of the primary fuel passage 22 face the fuel injection port 10a.

As shown in FIG. 4, the auxiliary fuel injection nozzle 12, which is a kind of spiral type fluid injection nozzle, has an auxiliary fuel (fluid) supply passage 38 extending in the direction of its axis C2. The downstream end of the auxiliary fuel supply passage 38 communicates with the auxiliary fuel ring passage 40. Specifically, a bottomed tubular cup 42 is formed at the downstream end of the auxiliary fuel injection nozzle 12. The bottom wall 42a of the cup 42 is formed at the upstream end of the cup 42, and the opening at the downstream end communicates with the fuel injection port 12a of the auxiliary fuel injection nozzle 12.

An annular gap 40 is formed between the peripheral wall 42b of the cup 42 and the peripheral wall 12b of the auxiliary fuel injection nozzle 12, and this gap 40 constitutes the auxiliary fuel annular passage 40. A plurality of communication holes 44 extending obliquely from the auxiliary fuel ring passage 40 toward the axis C2 are formed on the peripheral wall 42b of the cup 42. As shown in FIG. 5, these communication holes 44 constitute an auxiliary fuel swivel passage 44 for injecting the auxiliary fuel F0 while swirling around the axis C2.

The auxiliary fuel injection nozzle 12 is entirely formed of an integral body by three-dimensional modeling (3D printer). However, only the head 45 including the downstream part of the auxiliary fuel supply passage 38, the auxiliary fuel ring passage 40, and the auxiliary fuel swivel passage 44 shown in FIG. 4 is composed of an integral body by three-dimensional modeling, and the body excluding the head 45. The portion 46 may be formed by machining and both 45 and 46 may be brazed.

In the production of the fuel injection nozzle 10 of FIG. 1, the metal layer is formed by ejecting metal powder from a 3D printer from the base opposite to the head 20, and the metal layer is melted by irradiating a laser beam or an electron beam. By repeating the solidification, an integrated solidified portion is formed. The laser beam or electron beam is applied to a region corresponding to the shape of the fuel injection nozzle 10 in each metal layer based on the three-dimensional CAD data of the fuel injection nozzle 10.

Here, the main annular passage 28 of the head 20 of the fuel injection nozzle 10 in FIG. 2 and the inclined hole 30a of the main swivel passage 30 have a substantially circular or elliptical cross section. As a result, the passage resistance when the main fuel F2 flows through both passages 28 and 30 becomes smaller than when the cross section is rectangular. Further, in particular, when the main annular passage 28 is formed by using the three-dimensional laminated molding technique, as shown in the conventional example of FIG. 7, if the cross section of the main annular passage 28A of the head 20A is rectangular, the initial stage is It is necessary to prepare the support material SP in order to prevent the portion of the metal layer 51A to be formed that covers the main annular passage 28A from falling.

On the other hand, when the cross section of the main annular passage 28 of the head portion 20 is circular or elliptical as in the present embodiment shown in FIG. 6, the portion 28b facing the nozzle top surface 20a in this cross section is the nozzle top. Since the shape is curved so as to bulge toward the surface 20a, that is, toward the nozzle tip end, the upper metal layer 51 is sufficiently supported by the lower metal layer 51 even if the metal layer 51 is overlapped from the nozzle base end side. As a result, falls are avoided and, as a result, support is not required. This makes it possible to easily form the head 20 of the fuel injection nozzle 10 using a 3D printer.

Next, the operation of the combustor 1 of FIG. 1 will be described. When the gas turbine engine is started, the atomized primary fuel F1 injected from the fuel injection nozzle 10 into the combustion chamber 8 is mixed with the compressed air CA swirled by the swirler 16 to form a combustion region while swirling. The flame ignited by the spark plug 14 is maintained within this combustion region.

By passing through the main swivel passage 30, the main fuel F2 is injected from the fuel injection port 10a into the combustion chamber 8 while swirling around the nozzle axis C1. At this time, the main fuel F2 is mixed with the compressed air CA introduced into the nozzle air passage 17 near the outlet of the fuel injection port 10a, becomes atomized, and is injected into the combustion chamber 8 from the opening 15b. As a result, combustion is continued.

On the other hand, the auxiliary fuel F0 passes through the auxiliary fuel turning passage 44 of FIG. 4, and is injected in a mist form from the fuel injection port 12a into the combustion chamber 8 of FIG. 1 while turning around the axis C2.

According to the above configuration, at least the head 20 of the fuel injection nozzle 10 and at least the head 45 of the auxiliary fuel injection nozzle 12 are made of an integral body by three-dimensional modeling. As a result, the dimensional accuracy is high and the manufacturing becomes easy. Further, since the number of joints is reduced, fuel leakage can be prevented. Specifically, it is possible to avoid external leakage of the main fuel F2 and auxiliary fuel F0 due to poor joining, thermal expansion, etc., internal leakage of the primary fuel F1, and the like.

The present invention is not limited to the above embodiments, and various additions, changes, or deletions can be made without departing from the gist of the present invention. For example, the spiral injection nozzle of the above embodiment is a nozzle for injecting fuel, but the nozzle is not limited to this, and may be a cooling nozzle for injecting water. Further, the spiral injection nozzle of the present invention is not limited to the nozzle for a gas turbine engine. Therefore, such things are also included within the scope of the present invention.

10 Fuel injection nozzle (swirl type injection nozzle)
12 Auxiliary fuel injection nozzle (swirl type injection nozzle)
10a, 12a Fuel injection port 20 , 45 Head 20a Nozzle top surface 28, 34, 40 Circular passage 26, 38 Supply passage 30, 44 Swing passage 30a Inclined hole 30b Inclined chamber 36 Primary injection chamber C1 , C2 Nozzle axis

Claims (3)

A spiral injection nozzle (10) that injects fluid in a spiral shape through a fluid passage (24) .
The fluid passage (24) includes a swirling passage (30) that ejects the fluid while swirling around the nozzle axis (C1) , an annular passage (28) that supplies the fluid to the swirling passage (30) , and a nozzle. A supply passage (26) extending in the axial center (C1) direction to supply the fluid to the annular passage (28) is provided.
At least, the head (20) including the swivel passage (30) , the annular passage (28), and the downstream portion of the supply passage (26) is an integral body by three-dimensional modeling .
The passage cross section of the annular passage (28) is curved at least in the portion (28b) facing the nozzle top surface (20a).
A spiral injection nozzle in which the cross section of the annular passage (28) is circular or elliptical except for the nozzle radial inner portion (28a) connected to the swivel passage (30) . The spiral injection nozzle according to claim 1 , which forms a fuel injection nozzle for a gas turbine engine.
The fluid passage ( 24) is a main fuel passage formed at a position eccentric from the nozzle axis (C1) and extending in the axial direction.
In addition, it has a primary fuel passage (22)
The primary fuel passage (22) has a front bellflower supply passage (26) said nozzle axis (C1) is formed on the inside of the engine radial direction from extending in a direction the primary supply path (32), the primary supply passage It has a primary annular passage (34) that communicates with the downstream end of (32) and extends inward in the nozzle radial direction, and a primary injection chamber (36) that communicates with the downstream end of the primary annular passage (34) .
Said pivoting path (30) and the primary injection chamber (36) and said spiral jet nozzle that has to face the fuel injection port (10a) which is a type of fluid ejection port formed in the nozzle top surface (20a). In the spiral injection nozzle according to claim 2 , the swirling passage (30) of the main fuel passage (24) is located outside the nozzle radial direction of the primary injection chamber (36) of the primary fuel passage (22). In addition, the annular passage (28) has a plurality of inclined holes (30a) extending inward in the radial direction from the inside in the nozzle radial direction, and a conical tubular inclined chamber (30b) communicating downstream thereof.
The plurality of inclined holes (30a) are arranged apart from each other in the circumferential direction of the nozzle axis (C1) .
A spiral injection nozzle in which the downstream end of the inclined chamber (30b) communicates with the fuel injection port (10a) .

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