Intake strengthening method for flame tube of aero-engine

Abstract

The invention provides an aero-engine flame tube reinforced air inlet method, which is characterized in that an outer air inlet is designed, is integrally annular and is divided into a flow guide ring section, a mounting ring section and a middle transition section; the outer air inlet enables the mounting ring section to be assembled at the rear end of a main combustion hole in the outer wall face of the flame tube through a lengthened rivet, and meanwhile an injection sleeve is welded to the main combustion hole. When the aero-engine works, part of two air flows in a combustion chamber are blocked by the flow guide ring section under the influence of the internal and external pressure difference of the flame tube, so that the air pressure in the inlet area of the main combustion hole is enhanced. The combustor has the advantages that the air inlet effect is enhanced, the air inlet flow is increased, the air inlet penetration depth of the flame tube is increased, combustion is enhanced, the combustion efficiency is improved, the temperature field quality of an outlet of the combustion chamber is improved, and meanwhile the use safety of turbine parts is improved.

Description

Technical Field

[0001] This invention relates to the field of aero-engine flame tube technology, and in particular to a method for enhancing air intake in aero-engine flame tubes. Background Technology

[0002] When an aero-engine is operating, the gas in the two flow channels of the combustion chamber enters the flame tube through the main combustion holes on the outer wall, such as... Figure 1 As shown.

[0003] Due to the structure of the flame tube and the pressure difference between the inside and outside, the air penetration depth of the flame tube is insufficient, which cannot meet the requirements of the flame tube for combustion and mixing. This affects the combustion efficiency and the performance of the outlet temperature field, and at the same time makes it difficult to guarantee the safety of the turbine components. Summary of the Invention

[0004] The purpose of this invention is to propose a method for enhancing air intake in an aero-engine combustor. This method involves designing an external air intake, mounting it on the outer wall of the combustor, and using an ejector sleeve to allow two streams of air to effectively enter the combustor from the main combustion port, despite being blocked by the external air intake. This enhances the air intake effect, increases the air intake flow rate and penetration depth, strengthens combustion, improves combustion efficiency, and enhances the quality of the temperature field at the combustion chamber outlet, thereby improving the safety of turbine components.

[0005] This invention proposes a method for enhancing air intake in the combustor of an aero-engine. The method involves designing an external air intake, which is generally annular and consists of a guide ring section, an mounting ring section, and an intermediate transition section. The mounting ring section is assembled to the rear end of the main combustion port on the outer wall of the combustor using elongated rivets. Simultaneously, an ejector sleeve is welded to the main combustion port. During aero-engine operation, the two airflow streams in the combustion chamber are affected by the pressure difference inside and outside the combustor. Part of the air is blocked by the guide ring section, increasing the air pressure in the main combustion port inlet area and thus increasing the airflow rate. Combined with the ejector sleeve, this increases the airflow penetration depth and enhances the intake effect.

[0006] The aforementioned method for enhancing the air intake of an aero-engine flame tube can improve the air intake effect of the flame tube. The specific implementation method is as follows: The external air intake 1 is designed to be annular in shape, divided into a guide ring section 2, an installation ring section 3, and an intermediate transition section 4. The guide ring section 2 is a large-diameter annular tube structure; the installation ring section 3 is a small-diameter annular tube structure with rivet mounting holes 5 evenly distributed on it; the transition section 4 is a horn-shaped transition section between the guide ring section 2 and the installation ring section 3.

[0007] The external air inlet 1 is fitted with the mounting ring 3 to the rear end of the main combustion hole 8 on the outer wall of the flame tube 7 by means of the extended rivet 6, so as to ensure that the guide ring 2 is located above the main combustion hole 8.

[0008] The ejector sleeve 9 has a tubular structure with an air inlet flange 10 for easy air intake, and two lugs 11 on the edge for welding and fixing to the outer wall of the flame tube 7.

[0009] When an aero-engine is operating, the two airflows in the combustion chamber are affected by the pressure difference inside and outside the flame tube 7. Some of the air enters the flame tube 7 from the main combustion port 8. After the implementation of this invention, the air is blocked by the guide ring section 2, which increases the air density and pressure in the inlet area of ​​the main combustion port 8. Under the influence of the increased pressure difference, the airflow entering the flame tube 7 through the ejector sleeve 9 is relatively increased, the intake diffusion is relatively reduced, and the penetration depth is relatively increased. This strengthens the organization of combustion, improves combustion efficiency, enhances the quality of the temperature field at the combustion chamber outlet, and improves the safety of turbine components.

[0010] Advantages of this invention: This paper proposes a method for enhancing air intake in aero-engines via a flame tube, which improves the intake effect, increases the intake flow rate, increases the flame tube's air penetration depth, enhances combustion, improves combustion efficiency, improves the quality of the combustion chamber outlet temperature field, and simultaneously enhances the safety of turbine components. Attached Figure Description

[0011] Figure 1 Schematic diagram of the main combustion port air intake of the flame tube; Figure 2 This is a cross-sectional view of the external air intake. Figure 3 This is a structural diagram of the ejector sleeve; Figure 4 A diagram illustrating the application of the method; Figure 5 A schematic diagram illustrating the effect of the method implementation (airflow direction); In the diagram, 1-external air inlet, 2-guide ring section, 3-mounting ring section, 4-intermediate transition section, 5-rivet mounting hole, 6-extended rivet, 7-flame tube, 8-main combustion hole, 9-ejector sleeve, 10-flanged edge, 11-lug. Detailed Implementation

[0012] The present invention will be further explained below with reference to specific implementation schemes, but it is not limited to the present invention. The structures, proportions, sizes, etc. shown in the accompanying drawings are only used to complement the content disclosed in the specification, so as to enable those skilled in the art to understand and read, and are not intended to limit the conditions under which the present invention can be implemented. Therefore, they have no substantial technical significance. Any modification of the structure, change of the proportion relationship or adjustment of the size, without affecting the effect and purpose that the present invention can produce, should still fall within the scope of the technical content disclosed in the present invention.

[0013] This invention proposes a method for enhancing air intake in the combustor of an aero-engine. The method involves designing an external air intake, which is generally annular and consists of a guide ring section, an mounting ring section, and an intermediate transition section. The mounting ring section is assembled to the rear end of the main combustion port on the outer wall of the combustor using elongated rivets. Simultaneously, an ejector sleeve is welded to the main combustion port. During aero-engine operation, the two airflow streams in the combustion chamber are affected by the pressure difference inside and outside the combustor. Part of the air is blocked by the guide ring section, increasing the air pressure in the main combustion port inlet area and thus increasing the airflow rate. Combined with the ejector sleeve, this increases the airflow penetration depth and enhances the intake effect.

[0014] The aforementioned method for enhancing the air intake of the aero-engine flame tube can improve the air intake effect of the flame tube. The specific implementation method is as follows: The external air intake 1 is designed to be annular in shape, divided into a guide ring section 2, an installation ring section 3, and an intermediate transition section 4. The guide ring section 2 is a large-diameter annular tube structure; the installation ring section 3 is a small-diameter annular tube structure with rivet mounting holes 5 evenly distributed on it; the transition section 4 is a horn-shaped transition section between the guide ring section 2 and the installation ring section 3.

[0015] The external air inlet 1 is fitted with the mounting ring 3 to the rear end of the main combustion hole 8 on the outer wall of the flame tube 7 by means of the extended rivet 6, so as to ensure that the guide ring 2 is located above the main combustion hole 8.

[0016] The ejector sleeve 9 has a tubular structure with an air inlet flange 10 for easy air intake, and two lugs 11 on the edge for welding and fixing to the outer wall of the flame tube 7.

[0017] When an aero-engine is operating, the two airflows in the combustion chamber are affected by the pressure difference inside and outside the flame tube 7. Some of the air enters the flame tube 7 from the main combustion port 8. After the implementation of this invention, the air is blocked by the guide ring section 2, which increases the air density and pressure in the inlet area of ​​the main combustion port 8. Under the influence of the increased pressure difference, the airflow entering the flame tube 7 through the ejector sleeve 9 is relatively increased, the intake diffusion is relatively reduced, and the penetration depth is relatively increased. This strengthens the organization of combustion, improves combustion efficiency, enhances the quality of the temperature field at the combustion chamber outlet, and improves the safety of turbine components.

[0018] Matters not covered in this invention are common knowledge.

[0019] Although embodiments of the invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A method for enhancing air intake in an aero-engine flame tube, characterized in that: The aforementioned method for enhancing air intake in the aero-engine combustor involves designing an external air intake, which is annular in shape and divided into a guide ring section, an mounting ring section, and an intermediate transition section. The external air intake uses elongated rivets to assemble the mounting ring section to the rear end of the main combustion port on the outer wall of the combustor. Simultaneously, an ejector sleeve is welded to the main combustion port. During aero-engine operation, the two airflows in the combustion chamber, influenced by the pressure difference inside and outside the combustor, cause some air to be blocked by the guide ring section, increasing the air pressure in the main combustion port inlet area and thus increasing the intake flow rate. Combined with the ejector sleeve, this increases the intake penetration depth and enhances the intake effect.

2. The method for enhancing air intake in an aero-engine flame tube according to claim 1, characterized in that: The external air inlet (1) is annular in shape and is divided into a flow guide ring section (2), an installation ring section (3) and an intermediate transition section (4). The flow guide ring section (2) is a large-diameter annular tube structure; the installation ring section (3) is a small-diameter annular tube structure with rivet mounting holes (5) evenly distributed on it; the transition section (4) is a horn-shaped transition section between the flow guide ring section (2) and the installation ring section (3).

3. The method for enhancing air intake in an aero-engine flame tube according to claim 1, characterized in that: The external air inlet (1) is fitted with the mounting ring section (3) to the rear end of the main combustion hole (8) on the outer wall of the flame tube (7) by means of the extended rivet (6), so as to ensure that the guide ring section (2) is located above the main combustion hole (8).

4. The method for enhancing air intake in an aero-engine flame tube according to claim 1, characterized in that: The ejector sleeve (9) is a tubular structure with a flange (10) at the air inlet for easy air intake. It also has two lugs (11) at the edge for welding and fixing to the outer wall of the flame tube (7). When the aero-engine is working, the two airflows in the combustion chamber are affected by the pressure difference inside and outside the flame tube (7). Some air enters the flame tube (7) from the main combustion hole (8). The air is blocked by the guide ring section (2), which increases the air density and pressure in the inlet area of ​​the main combustion hole (8). Under the influence of the increased pressure difference, the airflow entering the flame tube (7) through the ejector sleeve (9) increases relatively, and the intake diffusion decreases relatively.

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