CN215112741U

CN215112741U - Novel aeroengine spouts oil ring

Info

Publication number: CN215112741U
Application number: CN202120823506.8U
Authority: CN
Inventors: 谢逸凡; 熊双; 屈帅镔; 胡晓安; 吴锦武; 向鑫; 孙海俊; 杨晓光; 贾杰; 刘奋成
Original assignee: Nanchang Hangkong University
Current assignee: Nanchang Hangkong University
Priority date: 2021-04-21
Filing date: 2021-04-21
Publication date: 2021-12-10
Anticipated expiration: 2031-04-21

Abstract

The utility model discloses a novel aircraft engine oil spray ring, which comprises an oil spray ring, wherein the oil spray ring is provided with an oil inlet pipe, the oil inlet pipe is symmetrically distributed on the oil spray ring, the oil spray ring is a symmetrical figure formed by alternately connecting a section of circular arc I on a ring I and a section of circular arc II on a ring II, the circular arc I is an eighth circular arc of the ring I, the circular arc II is an eighth circular arc of the ring II, the circular arc I is symmetrical about the circular arc II, the oil spray nozzles are symmetrically arranged on the oil spray ring and are distributed at the eighth equal parts of the ring I and the ring II, and the oil spray nozzles are connected with the oil inlet pipe through the oil spray ring, so that the utility model avoids the structural problem caused by the uneven arrangement of a fuel evaporation pipe at the back due to unequal distance optimization of the oil spray pipe, ensures that the oil spray amount of the oil spray nozzles is even, and improves the combustion performance of a combustion chamber, the method is beneficial to improving the overall performance of the turbojet engine.

Description

Novel aeroengine spouts oil ring

Technical Field

The utility model relates to an aeroengine spouts oil ring fuel injection system design field, especially relates to a novel aeroengine spouts oil ring.

Background

The oil injection ring is an important component in the turbojet engine, wherein the uniformity of the oil injection quantity of the oil injection needle determines the uniformity of a temperature field of the combustion chamber and is directly related to the combustion efficiency of the combustion chamber, so that the overall performance of the turbojet engine is also influenced. An optimization scheme of an oil injection pipe structure, which adopts 'oil injection needles are distributed at unequal intervals to improve oil injection uniformity along an annular space of an oil injection ring', is proposed in an article with the number of 1674 and 8190(2018) 03-382-06 in the aviation evolution. Although the method can improve the oil injection uniformity along the annular space of the oil injection ring, the overall structure of the micro-turbojet engine belongs to a highly symmetrical structure, and the position arrangement of the oil injection needles on the ring body can influence the position arrangement of the evaporation tubes symmetrically distributed in the combustion chamber to change. Meanwhile, the fuel concentration field of the atomized and evaporated fuel in the combustion chamber is inconsistent, so that the combustion efficiency is influenced. Therefore, a novel fuel injection ring of the aero-engine is provided.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to solve the technical problem who exists among the prior art, provide a novel aeroengine spouts oil ring.

In order to achieve the above purpose, the utility model provides a technical scheme is: the utility model provides a novel aeroengine spouts oil ring, includes and spouts the oil ring, it advances oil pipe to be provided with on the oil ring, it is in to advance oil pipe spout the last symmetric distribution of oil ring, spout the symmetrical figure that oil ring is connected in turn by one section circular arc one on annular one and one section circular arc two on the annular two and constitutes, circular arc one does the eighth circular arc of annular one, circular arc two is the eighth circular arc of annular two, just circular arc one is about circular arc bisymmetry, spout the symmetry on the oil ring and is provided with the fuel sprayer, the fuel sprayer distributes annular one with annular two's eighth branch department, the fuel sprayer pass through spout oil ring with it connects to advance oil pipe.

Preferably, the number of the oil nozzles arranged on the first arc and the second arc is eight, and the distribution positions are respectively the eight equal division points of the first annular part and the second annular part.

Preferably, the centers of the first arc and the second arc are respectively located on a line connecting the eight equal points of the first ring and the second ring with the centers of the circles, and the radius of the first arc and the second arc is the distance from the centers of the circles to the corresponding equal points.

The utility model discloses beneficial effect:

the utility model discloses well fuel sprayer symmetric distribution on spouting the oil ring has avoided spouting the structural problem that the inhomogeneous arrangement of the back fuel evaporating pipe that the equidistance optimization brought leads to for fuel sprayer fuel injection quantity is even, has improved the combustion performance of combustion chamber, helps improving the wholeness ability of turbojet engine.

Drawings

The accompanying drawings, which are described herein, serve to provide a further understanding of the invention and constitute a part of this specification, and the exemplary embodiments and descriptions thereof are provided for explaining the invention without unduly limiting it.

FIG. 1 is a schematic diagram of the overall structure of the preferred embodiment of the present invention;

fig. 2 is a side view of the preferred embodiment of the present invention.

The attached drawings are marked as follows:

1-oil inlet pipe 2-arc two 3-oil nozzle 4-annular one 5-annular two 6-arc one.

Detailed Description

This section will describe in detail the embodiments of the present invention, preferred embodiments of the present invention are shown in the attached drawings, which are used to supplement the description of the text part of the specification with figures, so that one can intuitively and vividly understand each technical feature and the whole technical solution of the present invention, but they cannot be understood as the limitation of the protection scope of the present invention.

In the description of the present invention, it should be understood that the orientation or positional relationship indicated with respect to the orientation description, such as up, down, front, rear, left, right, etc., is based on the orientation or positional relationship shown in the drawings, and is only for convenience of description and simplification of description, and does not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention.

In the description of the present invention, a plurality of means are one or more, a plurality of means are two or more, and the terms greater than, less than, exceeding, etc. are understood as not including the number, and the terms greater than, less than, within, etc. are understood as including the number. If the first and second are described for the purpose of distinguishing technical features, they are not to be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated or implicitly indicating the precedence of the technical features indicated.

In the description of the present invention, unless there is an explicit limitation, the words such as setting, installation, connection, etc. should be understood in a broad sense, and those skilled in the art can reasonably determine the specific meanings of the above words in combination with the specific contents of the technical solution.

Referring to fig. 1-2, according to a preferred embodiment of the present invention, a novel fuel injection ring for an aircraft engine includes a fuel injection ring, wherein a fuel inlet pipe 1 is disposed on the fuel injection ring, the fuel inlet pipe 1 is symmetrically distributed on the fuel injection ring, the fuel injection ring is a symmetrical pattern formed by alternately connecting a first section of circular arc 6 on a first ring 4 and a second section of circular arc 2 on a second ring, the first circular arc 6 is an eighth circular arc of the first ring 4, the second circular arc 2 is an eighth circular arc of the second ring 5, and the first circular arc 6 is symmetrical with respect to the second circular arc 2, the center of the first circular arc 6 is preferably located at 81.79mm from the eighth point of the first ring 4 to the center of the circle, and the center of the second circular arc 2 is preferably located at the intersection point of the second ring 5 eighth point and the center of the circle; the oil injection ring is symmetrically provided with oil injection nozzles 3, the oil injection nozzles 3 are distributed at the eight equal parts of the first annular part 4 and the second annular part 5, the oil injection nozzles 3 are connected with the oil inlet pipe 1 through the oil injection ring, the diameter D of the first annular part 4 is preferably 104.00mm, and the diameter D of the second annular part 5 is preferably 83.92 mm; when the first arc 6 and the second arc 2 are connected, the central angle of the first arc 6 is preferably 140.50 degrees, the central angle of the second arc 2 is preferably 95.50 degrees, the two arcs are symmetrical about the respective circle centers and the radius connecting line, and the oil nozzle 3 is connected with the oil inlet pipe 1 through an oil injection ring.

The utility model discloses in spout the oil ring and splice and adopt two oil pipes 1 that advance through circular arc 6 and two 2 symmetries of circular arc, both made spout the oil ring and go out oil quantity even, keep the structural symmetry who spouts the oil ring again, avoided the structural problem that leads to because of the inhomogeneous arrangement of the back fuel evaporating pipe that spouts the asymmetric bringing of oil ring for 3 fuel sprayer oil spouts oil quantity evenly, has improved the combustion performance of combustion chamber, helps improving the wholeness ability that the turbojet engine.

As a preferred embodiment of the present invention, it may also have the following additional technical features:

in this embodiment, the number of the oil spray nozzles 3 arranged on the first arc 6 and the second arc 2 is eight, and the distribution positions are respectively the eighth equal division points of the first ring 4 and the second ring 5, so that the uneven oil spray amount caused by the unequal distance of the oil spray nozzles 3 on the oil spray ring can be avoided, and the working efficiency can be improved.

In this embodiment, the centers of the first arc 6 and the second arc 2 are respectively located on a line connecting the eight equal points of the first ring 4 and the second ring 5 with the center of a circle, and the radii of the first arc 6 and the second arc 2 are distances from the center of a circle to the corresponding equal points; the radius of the first arc 6 is the distance from the circle center to the eighth bisector of the first ring 4, preferably 22.21mm, and the radius of the second arc 2 is the distance from the circle center to the eighth bisector of the second ring 5, preferably 20.8mm, so that the oil injection ring is more smoothly spliced.

The above additional technical features can be freely combined and used in superposition by those skilled in the art without conflict.

The above is only the preferred embodiment of the present invention, as long as the technical solution of the purpose of the present invention is realized by the substantially same means, all belong to the protection scope of the present invention.

Claims

1. The utility model provides a novel aeroengine spouts oil ring which characterized in that: the oil injection ring is provided with an oil inlet pipe (1), the oil inlet pipe (1) is symmetrically distributed on the oil injection ring, the oil injection ring is a symmetrical graph formed by alternately connecting a section of first arc (6) on a first annular part (4) and a section of second arc (2) on a second annular part (5), the first arc (6) is an eighth arc of the first annular part (4), the second arc (2) is an eighth arc of the second annular part (5), the first arc (6) is symmetrical about the second arc (2), the oil injection ring is symmetrically provided with oil injection nozzles (3), the oil injection nozzles (3) are distributed at the eighth equal division positions of the first annular part (4) and the second annular part (5), and the oil injection nozzles (3) are connected with the oil inlet pipe (1) through the oil injection ring.

2. The novel aeroengine oil spout ring of claim 1, characterized in that: the number of the oil nozzles (3) arranged on the first arc (6) and the second arc (2) is eight, and the distribution positions are respectively the eight equal division points of the first annular (4) and the second annular (5).

3. The novel aeroengine oil spout ring of claim 1, characterized in that: the circle centers of the first arc (6) and the second arc (2) are respectively positioned on a line connecting the eight equal points of the first ring (4) and the second ring (5) with the circle centers, and the radiuses of the first arc (6) and the second arc (2) are distances from the circle centers to the corresponding equal points.