Guide vane and turbojet engine

Abstract

The present invention discloses a guide vane and a turbojet engine. The guide vane body includes a guide vane inner ring and a guide vane outer ring fixedly mounted on the guide vane inner ring. An annular flow channel and a plurality of cooling flow channels are formed between the guide vane inner ring and the guide vane outer ring. The plurality of cooling flow channels are circumferentially distributed in a circle. The rear ends of the cooling flow channels are all connected to the annular flow channel. The guide vane outer ring is also provided with an oil inlet channel. The inner end of the oil inlet channel is connected to the annular flow channel. The guide vane outer ring also includes an oil inlet pipe and a plurality of fuel branch pipes. The oil inlet pipe is connected to the outer end of the oil inlet channel. The fuel branch pipes are installed on the guide vane body and are connected to the front ends of the cooling flow channels in a one-to-one correspondence. The present invention improves the structure of the guide vane and uses regenerative cooling technology to cool the guide vane, thereby improving the heat resistance of the guide vane, extending its service life, and improving the overall performance of the turbojet engine.

Description

Technical Field

[0001] The present invention relates to the technical field of engines, and in particular to a guide vane and a turbojet engine. Background Art

[0002] As an important component of a turbojet engine, the guide vane is generally installed at the rear of the combustion chamber. It is used to deflect the direction and reduce the pressure and speed of the high-temperature combustion gas inside the engine, thereby forming a high-speed rotating high-temperature airflow to drive the turbine to rotate. Therefore, the guide vane usually needs to withstand high-temperature combustion gas of thousands of degrees and 4-6 times the atmospheric pressure. Due to the limitations of the inherent properties of the material itself, it is difficult to improve the temperature resistance of the material itself, which limits the improvement of the heat resistance of the guide vane and also limits the improvement of the overall performance of the turbojet engine. Summary of the Invention

[0003] The purpose of the present invention is to provide a guide, which improves the heat resistance of the guide through structural improvement, prolongs the service life, and improves the overall performance of the turbojet engine.

[0004] Another object of the present invention is to provide a turbojet engine with good overall performance.

[0005] In order to solve the above technical problems, the present invention provides a guide, including a guide body, the guide body including a guide inner ring, and a guide outer ring fixedly mounted on the guide inner ring, an annular flow channel and a plurality of cooling flow channels are formed between the guide inner ring and the guide outer ring, the plurality of cooling flow channels are distributed in a circle along the circumferential direction, the rear ends of the cooling flow channels are all connected to the annular flow channel, the guide outer ring is further provided with an oil inlet channel, the inner end of the oil inlet channel is connected to the annular flow channel,

[0006] It also includes an oil inlet pipe and a plurality of fuel branch pipes, wherein the oil inlet pipe is connected to the outer end of the oil inlet channel, and the fuel branch pipes are installed on the guide body and are connected to the front end of the cooling channel in a one-to-one correspondence.

[0007] The guide of the present invention adopts a combined structure of inner and outer rings, which facilitates the processing of annular flow channels and cooling flow channels between the inner ring and the outer ring of the guide, reducing the processing difficulty and reducing the processing cost; at the same time, the oil inlet pipe, the fuel branch pipe and the guide body are integrated into one, and the annular flow channel serves as the main channel, connecting the oil inlet channel and the cooling flow channels. During operation, the flow path of the fuel is as follows: the fuel first enters the oil inlet channel through the oil inlet pipe, then enters the annular flow channel, and is distributed to the inside of each cooling flow channel, and finally is sprayed into the combustion chamber through each fuel branch pipe to participate in the combustion reaction.

[0008] As can be seen from the above, the guide of the present invention adopts regenerative cooling technology, using fuel as a coolant to cool the guide. On the one hand, it reduces the temperature of the guide, thereby reducing the requirements for the high temperature resistance and structural strength of the guide material, reducing material costs, improving the high temperature performance of the guide, and increasing its service life, thereby improving the overall performance of the turbojet engine; on the other hand, it does not need to add additional coolant weight, so it does not increase the total weight of the engine, and improves the thrust-to-weight ratio of the engine; at the same time, the fuel is preheated before being sprayed into the combustion chamber for combustion reaction, so that the atomization effect of the fuel is better, the combustion is more complete, and the combustion efficiency of the engine is improved. In addition, the oil inlet pipe, the fuel branch pipe and the guide body are integrated into one body, which is convenient for installation and reliable connection compared with the prior art of fixing the fuel pipe clamp to the combustion chamber.

[0009] Optionally, the outer peripheral wall of the guide inner ring is provided with an annular groove and a plurality of cooling grooves. After the guide outer ring is fitted onto the guide inner ring, the annular groove forms the annular flow channel, and the cooling grooves form the cooling flow channel.

[0010] Optionally, the inner ring of the guide includes a first ring body and a first flange connected to the rear end of the first ring body, and the outer ring of the guide includes a second ring body and a second flange connected to the rear end of the second ring body. The second ring body is mounted on the first ring body to form the annular flow channel and the cooling flow channel. The first flange and the second flange are sealed and fixedly connected, and the oil inlet channel is arranged on the second flange.

[0011] Optionally, one of the side walls opposite to the first flange and the second flange is provided with at least one annular mounting groove and further includes an annular sealing ring, which is correspondingly installed in the annular mounting groove and abuts against the other one.

[0012] Optionally, the oil inlet channel is L-shaped, and includes a first channel and a second channel that are interconnected, the first channel extends radially, and the second channel extends axially toward the front end.

[0013] Optionally, the cooling channel extends in a serpentine shape.

[0014] Optionally, the outer wall of the guide outer ring gradually tilts inwards as it approaches the front end;

[0015] And / or, along the direction gradually approaching the front end, the inner wall of the inner ring of the guide gradually tilts outward.

[0016] Optionally, the fuel branch pipe is fixed to the cooling channel by welding.

[0017] Optionally, the oil inlet pipe is fixed to the oil inlet channel by welding.

[0018] The present invention also provides a turbojet engine comprising the aforementioned guide vane.

[0019] The turbojet engine of the present invention includes the aforementioned guide vane, and therefore has the same technical effects as the aforementioned guide vane, which will not be described in detail here. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 A schematic structural diagram of a specific embodiment of the guide provided by the present invention;

[0021] Figure 2 for Figure 1 A partial enlarged view of the guide at the oil inlet;

[0022] Figure 3 for Figure 1 A partial enlarged view of the guide at the oil outlet;

[0023] Figure 4 for Figure 1 A schematic diagram of the structure of the inner ring of the guide in the guide;

[0024] Figure 5 for Figure 4 A partial enlarged view of the inner ring of the guide;

[0025] in, Figure 1-Figure 5 The reference numerals in the figures are described as follows:

[0026] 1-guide body; 11-guide inner ring; 111-first ring body; 112-first flange; 12-guide outer ring; 121-second ring body; 122-second flange; 13-annular sealing ring; 2-fuel inlet pipe; 3-fuel branch pipe;

[0027] a-annular flow channel; b-cooling flow channel; c-oil inlet channel; a'-annular groove; b'-cooling groove. DETAILED DESCRIPTION

[0028] In order to enable those skilled in the art to better understand the technical solution of the present invention, the present invention is further described in detail below with reference to the accompanying drawings and specific embodiments.

[0029] The words "first", "second", etc. mentioned in this article are only used to facilitate the description of two or more structures or components with the same or similar structures and / or functions, and do not mean any special limitation on the order and / or importance.

[0030] Herein, the term "plurality" refers to an indefinite number, usually more than two.

[0031] In this article, "front end" refers to the end axially close to the combustion chamber after the guide vane is installed in the turbojet engine; "rear end" refers to the end axially close to the turbine; "inner end" refers to the end radially close to the middle of the guide vane; and "outer end" refers to the end radially away from the middle of the guide vane.

[0032] In this article, the direction of the arrow is the flow direction of the fuel.

[0033] Please refer to Figure 1-Figure 3 , Figure 1 A schematic structural diagram of a specific embodiment of the guide provided by the present invention; Figure 2 for Figure 1 A partial enlarged view of the guide at the oil inlet; Figure 3 for Figure 1 A partial enlarged view of the guide at the oil outlet.

[0034] The present invention provides a guide, including a guide body 1, the guide body 1 including a guide inner ring 11, and a guide outer ring 12 fixedly mounted on the guide inner ring 11, an annular flow channel a and a plurality of cooling flow channels b are formed between the outer circumferential wall of the guide inner ring 11 and the inner circumferential wall of the guide outer ring 12, the plurality of cooling flow channels b are distributed in a circle along the circumferential direction, the rear ends of the cooling flow channels b are all connected to the annular flow channel a, the guide outer ring 12 is further provided with an oil inlet channel c, the inner end of the oil inlet channel c is connected to the annular flow channel a,

[0035] It also includes an oil inlet pipe 2 and multiple fuel branch pipes 3. The oil inlet pipe 2 is connected to the outer end of the oil inlet channel c. The fuel branch pipes 3 are installed on the guide body 1 and are connected to the front end of the cooling flow channel b in a one-to-one correspondence.

[0036] The guide of the present invention adopts a combined structure of inner and outer rings, which facilitates the processing of the annular flow channel a and the cooling flow channel b between the inner ring 11 and the outer ring 12 of the guide, reducing the processing difficulty and processing cost; at the same time, the oil inlet pipe 2, the fuel branch pipe 3 and the guide body 1 are integrated into one body, and the annular flow channel a serves as the main channel, connecting the oil inlet channel c and the cooling flow channels b. During operation, the flow path of the fuel is as follows: the fuel first enters the interior of the oil inlet channel c through the oil inlet pipe 2, then enters the annular flow channel a, and is distributed to the interior of each cooling flow channel b, and finally is sprayed into the interior of the combustion chamber through each fuel branch pipe 3 to participate in the combustion reaction.

[0037] As can be seen from the above, the guide of the present invention adopts regenerative cooling technology, using fuel as a coolant to cool the guide. On the one hand, it reduces the temperature of the guide, thereby reducing the requirements for the high temperature resistance and structural strength of the guide material, reducing material costs, improving the high temperature performance of the guide, and increasing its service life, thereby improving the overall performance of the turbojet engine; on the other hand, it does not need to add additional coolant weight, so it does not increase the total weight of the engine, and improves the thrust-to-weight ratio of the engine; at the same time, the fuel is preheated and then sprayed into the combustion chamber for combustion reaction, so that the atomization effect of the fuel is better, the combustion is more complete, and the combustion efficiency of the engine is improved. In addition, the oil inlet pipe 2, the fuel branch pipe 3 and the guide body 1 are integrated into one body, which is convenient for installation and reliable connection compared with the prior art of fixing the fuel pipe clamp to the combustion chamber.

[0038] In this embodiment, the number of cooling channels b is 16, and they are distributed circumferentially in a circle, so that all circumferential parts of the guide body 1 can be evenly cooled; at the same time, the number of fuel branch pipes 3 is also 16, and they are also distributed circumferentially in a circle, so that the fuel is injected into the combustion chamber more evenly, thereby making the combustion more complete and improving the combustion efficiency of the engine.

[0039] Please refer to Figure 4-Figure 5 , Figure 4 for Figure 1 A schematic diagram of the structure of the inner ring of the guide in the guide; Figure 5 for Figure 4 A partial enlarged view of the inner ring of the guide.

[0040] In this embodiment, the outer peripheral wall of the guide inner ring 11 is provided with an annular groove a' and a plurality of cooling grooves b'. The plurality of cooling grooves b' are distributed along the circumferential direction. After the guide outer ring 12 is fitted onto the guide inner ring 11, the annular groove a' forms the aforementioned annular flow channel a, and the cooling grooves b' form the aforementioned cooling flow channel b.

[0041] It is understood that in actual applications, it is feasible to provide the annular groove a' and the cooling groove b' on the inner circumferential wall of the guide outer ring 12, or to provide them on both the outer circumferential wall of the guide inner ring 11 and the inner circumferential wall of the guide outer ring 12. Of course, in this embodiment, the annular groove a' and the cooling groove b' are provided on the outer circumferential wall of the guide inner ring 11, which facilitates processing and is a more preferred technical solution.

[0042] Please continue to refer to Figure 1In this embodiment, the guide inner ring 11 includes a first ring body 111 and a first flange 112 connected to the rear end of the first ring body 111. The guide outer ring 12 includes a second ring body 121 and a second flange 122 connected to the rear end of the second ring body 121. The second ring body 121 is mounted on the first ring body 111, and the aforementioned annular flow channel a and cooling flow channel b are formed therebetween. The first flange 112 and the second flange 122 are sealed and fixedly connected, and the oil inlet channel c is arranged on the second flange 122.

[0043] Among them, the first flange 112 and the second flange 122 are sealed and fit together. Specifically, an annular mounting groove can be set in the opposite side walls of the first flange 112 and the second flange 122, and an annular sealing ring 13 is also included. The annular sealing ring 13 is installed in the annular mounting groove and abuts against the other one to achieve sealing and prevent oil leakage.

[0044] It is understandable that there is no limit to the number of the annular mounting groove and the annular sealing ring 13 , and there can be at least one as long as the sealing effect can be guaranteed.

[0045] Please combine Figure 2 It is understood that in this embodiment, the oil inlet channel c is L-shaped and includes a first channel and a second channel that are interconnected. The first channel extends radially, and the second channel extends axially toward the front end. Of course, the specific structure of the oil inlet channel c is not limited, as long as it can connect the oil inlet pipe 2 and the annular flow channel a. For example, the oil inlet channel c may only include the first channel that extends radially.

[0046] Please continue to refer to Figure 4-Figure 5 In this embodiment, the cooling channel b extends in a serpentine shape. This extends the fuel flow path through the cooling channel b, improving the heat exchange efficiency between the fuel and the guide body 1. This ensures good cooling of the guide body 1 and enhances fuel atomization.

[0047] Please continue to refer to Figure 3 In this embodiment, as the direction gradually approaches the front end, the outer wall of the guide outer ring 12 gradually tilts inward, and the inner wall of the guide inner ring 11 gradually tilts outward, thus forming two inclined guide surfaces. The high-temperature combustion gas generated after combustion in the combustion chamber can flow backward along the guide surfaces, further preheating the fuel inside the cooling flow channel b, improving its atomization effect, making the combustion more complete, and thus improving the combustion efficiency of the engine.

[0048] In addition, in this embodiment, the fuel branch pipe 3 is fixed to the cooling flow channel b by welding; the oil inlet pipe 2 is fixed to the oil inlet channel c by welding, and the connection is reliable.

[0049] The present invention also provides a turbojet engine comprising the aforementioned guide vane.

[0050] The turbojet engine of the present invention includes the aforementioned guide vane, and therefore has the same technical effects as the aforementioned guide vane, which will not be described in detail here.

[0051] The above describes in detail the guide vane and turbojet engine provided by the present invention. Specific examples are used herein to illustrate the principles and implementation methods of the present invention. The description of the above embodiments is intended only to facilitate understanding of the method and core concepts of the present invention. It should be noted that those skilled in the art may make various improvements and modifications to the present invention without departing from the principles of the present invention, and such improvements and modifications fall within the scope of protection of the claims of the present invention.

Claims

1. A guide, characterized in that: The invention comprises a guide body (1), wherein the guide body (1) comprises a guide inner ring (11), and a guide outer ring (12) fixedly mounted on the guide inner ring (11), an annular flow channel (a) and a plurality of cooling flow channels (b) are formed between the outer peripheral wall of the guide inner ring (11) and the inner peripheral wall of the guide outer ring (12), wherein the plurality of cooling flow channels (b) are distributed in a circle along the circumferential direction, and the rear ends of the cooling flow channels (b) are all connected to the annular flow channel (a), and the guide outer ring (12) is further provided with an oil inlet channel (c), the inner end of the oil inlet channel (c) is connected to the annular flow channel (a), It also includes an oil inlet pipe (2) and a plurality of fuel branch pipes (3), wherein the oil inlet pipe (2) is connected to the outer end of the oil inlet channel (c), and the fuel branch pipes (3) are installed on the guide body (1) and are connected to the front end of the cooling flow channel (b) in a one-to-one correspondence; As it approaches the front end, the outer wall of the guide outer ring (12) gradually tilts inwards; And / or, along the direction gradually approaching the front end, the inner wall of the guide inner ring (11) gradually tilts outward.

2. The guide according to claim 1, characterized in that: The outer peripheral wall of the guide inner ring (11) is provided with an annular groove (a') and a plurality of cooling grooves (b'); after the guide outer ring (12) is fixedly mounted on the guide inner ring (11), the annular groove (a') forms the annular flow channel (a), and the cooling grooves (b') form the cooling flow channel (b).

3. The guide according to claim 1, characterized in that: The guide inner ring (11) includes a first ring body (111) and a first flange (112) connected to the rear end of the first ring body (111); the guide outer ring (12) includes a second ring body (121) and a second flange (122) connected to the rear end of the second ring body (121); the second ring body (121) is fitted onto the first ring body (111), and the annular flow channel (a) and the cooling flow channel (b) are formed therebetween; the first flange (112) and the second flange (122) are sealed and fixedly connected; and the oil inlet channel (c) is provided on the second flange (122).

4. The guide according to claim 3, characterized in that: One of the opposite side walls of the first flange (112) and the second flange (122) is provided with at least one annular mounting groove and also includes an annular sealing ring (13). The annular sealing ring (13) is correspondingly installed in the annular mounting groove and abuts against the other.

5. The guide according to claim 3, characterized in that: The oil inlet channel (c) is L-shaped and includes a first channel and a second channel that are interconnected. The first channel extends radially, and the second channel extends axially toward the front end.

6. The guide according to any one of claims 1 to 5, characterized in that: The cooling channel (b) extends in a serpentine shape.

7. The guide according to any one of claims 1 to 5, characterized in that: The fuel branch pipe (3) is fixed to the cooling channel (b) by welding.

8. The guide according to any one of claims 1 to 5, characterized in that: The oil inlet pipe (2) is fixed to the oil inlet channel (c) by welding.

9. A turbojet engine, characterized in that: The guide comprises the guide described in any one of claims 1 to 8.

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