CN112577069B - Oblique flow combustion chamber side wall surface structure suitable for small head inclination angle - Google Patents
Oblique flow combustion chamber side wall surface structure suitable for small head inclination angle Download PDFInfo
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- CN112577069B CN112577069B CN202011493571.5A CN202011493571A CN112577069B CN 112577069 B CN112577069 B CN 112577069B CN 202011493571 A CN202011493571 A CN 202011493571A CN 112577069 B CN112577069 B CN 112577069B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/002—Wall structures
Abstract
The invention relates to a sidewall structure of an oblique flow combustion chamber suitable for a small head inclined angle, which can enhance the stability of flame of the combustion chamber. The side wall surface structure is special for the oblique flow combustion chamber under a small inclination angle, and is formed by splicing a flat plate with cooling holes and a concave plate, wherein the cooling holes in the flat plate form a certain angle with the flat plate, and the cooling holes in adjacent rows are arranged in a staggered manner; the section of the concave plate is in a concave shape, and the concave plate and the flat plate with the cooling hole form a rectangular cooling channel. The rectangular cooling channel composed of flat plate and concave plate is positioned in the combustion chamber at the joint of two ends, the velocity distribution of the region is changed, thereby the vortex is generated near the side wall surface to enhance flame holding, and the cold air flows into the side wall surface from the cooling channel for convection cooling. Through the structure of the side wall surface, the structure can play a role in rectifying the oblique flow combustion chamber with the small head inclined angle, so that the structure of a backflow area in the combustion chamber becomes complete, the stability of flame is further enhanced, and the stable combustion boundary of the combustion chamber is effectively widened.
Description
Technical Field
The invention relates to the field of design of aero-engine combustors, in particular to a side wall surface structure of an oblique flow combustor, which is a structure for widening a stable combustion boundary and enhancing flame stability, and particularly relates to a side wall surface structure of an oblique flow combustor applied to a small head part under an oblique angle.
Background
In an aircraft engine, air is pressurized by a compressor, and then the air direction is adjusted to be axial by a last stage guide vane of the compressor so as to enter a combustion chamber. In the combustion chamber, a fuel injection system injects oil into high-pressure air flow and ignites and burns, high-temperature and high-pressure gas is formed after burning, the flowing direction of the air flow is further adjusted through a turbine inlet guide vane, and finally the air flow pushes a turbine movable vane to do work. In order to further improve the thrust-weight ratio of an aircraft engine, related researchers have proposed a non-axial air-intake diagonal flow combustion chamber structure which is expected to reduce or even eliminate the number of guide vanes at the outlet of a compressor and the inlet of a turbine. At the same time, the pneumatic loss is correspondingly reduced due to the reduction of the number of guide vanes. On the other hand, a reduction in the number of turbine inlet vanes may also correspondingly reduce the amount of cooling air required by the turbine. However, because the flame tube heads of the oblique flow combustion chamber are connected by the side plates, the structure of the backflow zone inside the oblique flow combustion chamber is related to the included angle alpha between the flame tube heads and the axis of the combustion chamber. When the alpha is larger than 38 degrees, the interior of the combustion chamber is of a complete backflow zone structure, the flame stability of the combustion chamber is strong, but the interference between adjacent cyclones is caused by the overlarge alpha, and the realization is difficult in engineering practice; when alpha is less than 38 degrees, the adjacent cyclones are far away from each other, interference is avoided, and engineering application can be met, but at the moment, the structure of a backflow area in the combustion chamber is incomplete, and the stability of flame is poor.
In order to solve the problem that the backflow zone in the oblique flow combustion chamber is incomplete under the small head inclination angle, a new structural design needs to be carried out on the side wall surface of the combustion chamber. Because swirl is widely adopted in the combustion chamber to stabilize flame, if the side wall faces the swirl to generate symmetrical constraint through a new design, the pressure distribution in the combustion chamber can be changed, the negative pressure area is enlarged, a complete backflow area can be formed, and the stability of flame is improved and the flammability boundary is widened.
Disclosure of Invention
Aiming at the defects and shortcomings of the existing inclined-flow combustion chamber structure, the invention provides the side wall surface structure of the inclined-flow combustion chamber suitable for the inclined angle of the small head.
In order to achieve the technical purpose, the inclined flow combustion chamber structure is realized by the following technical scheme:
the utility model provides a skew flow combustion chamber lateral wall structure suitable for under little head angle of inclination, includes a foraminiferous flat board and a notch plate, its characterized in that:
a plurality of rows of cooling holes are formed in the perforated flat plate in an array arrangement, an included angle is formed between the normal direction of each cooling hole and the normal direction of the perforated flat plate, and the cooling holes in adjacent rows are arranged in a staggered manner;
the cross section of the concave plate is at least basically concave, and the concave plate comprises a bottom plate and two side plates positioned on the left side and the right side of the width direction of the bottom plate;
the length of the flat plate with holes is greater than that of the concave plate, and the flat plate with holes is fixedly arranged at the tops of the left side plate and the right side plate of the concave plate in a mode that one end of the flat plate with holes in the length direction is aligned with the concave plate, so that a cooling channel is formed by the bottom plate, the left side plate and the right side plate of the concave plate and the flat plate with holes;
the concave plate is completely inserted into the flame tube at the junction of the two ends of the oblique flow combustion chamber, the other end of the perforated flat plate is just opposite to the incoming flow direction and is flush with the head panel of the combustion chamber, one part of cooling air enters the oblique flow combustion chamber from the cooling channel and carries out convection cooling on the bottom plate of the concave plate, and the other part of cooling air passes through the cooling holes in the perforated flat plate to carry out cooling protection on the flat plate.
Preferably, the length L of the concave plate1Is the length L of the perforated flat plate2The height h of the side surface of the concave plate is 1-2 mm, and the thickness of the concave plate and the perforated plate is 1.5-2 mm.
Preferably, the thickness of the concave plate and the perforated flat plate is consistent with that of the head panel of the combustion chamber, namely the width d of the perforated flat plate1Width d of bottom surface of concave plate2The relationship between them is: d1＝d2H is the head height of the combustion chamber.
Preferably, the height h of the side surface of the concave plate is 1-2 mm.
Preferably, the diameter of the cooling holes in the flat plate with holes is 1.5-2 mm, and the included angle between the normal direction of the cooling holes and the normal direction of the flat plate with holes is 45-60 degrees.
Preferably, the length L of the perforated plate2Comprises the following steps:
L2＝H tanα
h is the height of the head of the combustion chamber, alpha is an included angle between the head of the flame tube in the oblique flow combustion chamber and the axis of the combustion chamber, and the definition formula of alpha is as follows:
wherein beta is the geometric angle of the outlet of the last-stage movable blade of the compressor, w is the relative speed of the outlet airflow, and c is the absolute speed of the outlet airflow.
Preferably, the head of the oblique flow combustion chamber is inclined at an angle α of less than 38 °.
The invention relates to a sidewall structure of an oblique flow combustion chamber suitable for a small head inclination angle, which has the working principle that: when the side wall surface is installed, the concave plate is completely inserted into the flame tube at the junction of the two ends of the combustion chamber. When the upstream incoming air encounters the side wall surface, the side wall surface has a cooling passage through which the air flows into the combustion chamber for convection cooling of the concave plate, and another portion of the air passes through the cooling holes in the perforated plate for cooling protection of the plate. The concave plate completely inserted into the flame tube hinders circumferential expansion of rotational flow from the swirler, so that a stationary vortex is formed near the side wall surface, and a complete backflow area structure is formed, and the complete backflow area structure provides a wide low-speed area and high-temperature burned products for flame stabilization, thereby being beneficial to enhancing the stability of the flame and widening a stable combustion boundary of the combustion chamber.
Compared with the side wall surface of the existing oblique flow combustion chamber, the side wall surface structure of the oblique flow combustion chamber suitable for the small-head inclination angle has the obvious technical effects that the side wall surface structure can generate symmetrical constraint on swirl, changes the radial distribution of pressure and increases the area of an internal backflow zone of the combustion chamber, and the cooling holes and the rectangular grooves carry out convection cooling and gas film cooling protection on the side wall surface, so that the aim of enhancing the flame stability of the oblique flow combustion chamber of the aero-engine under the small-head inclination angle is finally achieved, and the stable combustion boundary of the combustion chamber is effectively widened.
Drawings
FIG. 1 is a schematic view of the sidewall structure of a mixed-flow combustor suitable for use at small head inclination angles according to the present invention.
Fig. 2 is a dimensional schematic diagram of portions in a cross section of a side wall surface of a combustor of the present invention.
FIG. 3 is a schematic structural view of the sidewall structure of the combustion chamber disposed in the mixed-flow combustion chamber according to the present invention.
FIG. 4 is a schematic structural diagram of a conventional combustor sidewall structure disposed in a mixed-flow combustor.
The reference numerals in the figures are illustrated as follows:
1. a concave plate; 2. a perforated plate; 3. and cooling the holes.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the following embodiments are made with reference to the accompanying drawings
As shown in FIGS. 1 and 2, the structure of the sidewall of the oblique flow combustion chamber of the present invention, which is suitable for small head inclination angles, comprises a concave plate 1, a perforated flat plate 2, and cooling holes 3 on the flat plate; the concave plate 1 and the perforated flat plate 2 have the same thickness; the concave plate 1 is connected with the perforated flat plate 2 at the tail end in a flush manner, and the perforated flat plate 2 is parallel to the airflow direction; one end of the concave plate facing the airflow is connected with the end wall of the head in a flush manner; the length of the perforated flat plate is twice that of the concave plate, the diameter of the cooling holes 3 on the perforated flat plate is 1.5mm, the inclination angle of the cooling holes is 60 degrees, and 10 groups are distributed along the air flow direction.
More specifically, in the structure of the side wall surface of the oblique flow combustion chamber suitable for the small head part under the inclination angle, a plurality of rows of cooling holes 3 are arranged on the perforated flat plate 2 in an array manner, the normal direction of each cooling hole 3 and the normal direction of the perforated flat plate 2 form an included angle, and the cooling holes 3 in each adjacent row are staggered; the cross section of the concave plate 1 is at least basically concave, and comprises a bottom plate and two side plates positioned on the left side and the right side of the width direction of the bottom plate; the length of the flat plate with holes 2 is greater than that of the concave plate 1, and the flat plate with holes 2 is fixedly arranged on the tops of the left side plate and the right side plate of the concave plate 1 in a mode that one end of the flat plate with holes in the length direction is aligned with the concave plate 1, so that a cooling channel is formed by the bottom plate, the left side plate and the right side plate of the concave plate 1 and the flat plate with holes 2; inside the concave plate 1 inserted the flame tube of oblique flow combustion chamber both ends juncture completely, the other end of foraminiferous flat board 2 then just is just coming the flow direction and is leveled with combustion chamber head panel, and partly cooling air gets into the oblique flow combustion chamber from cooling channel, carries out convection cooling to the bottom plate of concave plate 1, and another part cooling air then passes the cooling hole 3 in the foraminiferous flat board 2 and protects the flat cooling.
Preferably, in the structure of the side wall surface of the oblique flow combustion chamber suitable for the small head inclination angle, the length L of the concave plate 11Is a length L of the perforated flat plate 22The height h of the side surface of the concave plate is 1-2 mm, and the thickness of the concave plate and the perforated plate is 1.5-2 mm. The thickness of the concave plate 1 and the perforated flat plate 2 is consistent with that of the head panel of the combustion chamber. The height h of the side surface of the concave plate 1 is 1-2 mm. The diameter of the cooling hole on the flat plate with holes 2 is 1.5-2 mm, and the inclination angle is 60 degrees. Length L of perforated plate 22Comprises the following steps: l2H tan α, where H is the height of the combustion chamber head, α is the angle between the flame tube head and the combustion chamber axis in the mixed-flow combustion chamber, and α is defined as:
wherein β is the geometric angle of the outlet of the last-stage movable blade of the compressor, w is the relative velocity of the outlet airflow, and c is the absolute velocity of the outlet airflow, as shown in fig. 4.
The invention relates to a sidewall structure of an oblique flow combustion chamber suitable for a small head inclination angle, which has the working principle that: as shown in FIG. 3, the sidewall surface structure of the present invention is installed with the concave plate fully inserted into the interior of the liner at the intersection of the two ends of the combustion chamber. When the upstream incoming air meets the side wall surface, the air flow passes through the cooling channel to enter the combustion chamber due to the existence of the cooling channel on the side wall surface, so as to carry out convection cooling on the concave plate 1, and the other part of the air passes through the cooling holes 3 in the perforated flat plate 2 to carry out cooling protection on the flat plate. The concave plate completely inserted into the flame tube hinders circumferential expansion of rotational flow from the swirler, so that a stationary vortex is formed near the side wall surface, and a complete backflow area structure is formed, and the complete backflow area structure provides a wide low-speed area and high-temperature burned products for flame stabilization, thereby being beneficial to enhancing the stability of the flame and widening a stable combustion boundary of the combustion chamber.
The present invention is not limited to the above preferred embodiments, but rather, any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the scope of the present invention.
Claims (6)
1. The utility model provides a skew flow combustion chamber lateral wall structure suitable for under little head angle of inclination, includes a foraminiferous flat board and a notch plate, its characterized in that:
a plurality of rows of cooling holes are formed in the perforated flat plate in an array arrangement, an included angle is formed between the normal direction of each cooling hole and the normal direction of the perforated flat plate, and the cooling holes in adjacent rows are arranged in a staggered manner;
the cross section of the concave plate is at least basically concave, and the concave plate comprises a bottom plate and two side plates positioned on the left side and the right side of the width direction of the bottom plate;
the length of the flat plate with holes is greater than that of the concave plate, and the flat plate with holes is fixedly arranged at the tops of the left side plate and the right side plate of the concave plate in a mode that one end of the flat plate with holes in the length direction is aligned with the concave plate, so that a cooling channel is formed by the bottom plate, the left side plate and the right side plate of the concave plate and the flat plate with holes;
the concave plate is completely inserted into the flame tube at the junction of the two ends of the oblique flow combustion chamber, the other end of the perforated flat plate is just opposite to the incoming flow direction and is flush with the head panel of the combustion chamber, one part of cooling air enters the oblique flow combustion chamber from the cooling channel and carries out convection cooling on the bottom plate of the concave plate, and the other part of cooling air passes through the cooling holes in the perforated flat plate to carry out cooling protection on the flat plate.
2. The sidewall surface structure of claim 1, wherein the length L of the gib plate1Is the length L of the perforated flat plate2The height h of the side surface of the concave plate is 1-2 mm, and the thickness of the concave plate and the plate with the hole is 1.5-2 mm.
3. The sidewall surface structure of claim 2, wherein the length L of the perforated flat plate2Comprises the following steps:
L2＝H tanα
h is the height of the head of the combustion chamber, alpha is an included angle between the head of the flame tube in the oblique flow combustion chamber and the axis of the combustion chamber, and the definition formula of alpha is as follows:
wherein beta is the geometric angle of the outlet of the last-stage movable blade of the compressor, w is the relative speed of the outlet airflow, and c is the absolute speed of the outlet airflow.
4. The sidewall surface structure of claim 3, wherein the perforated flat plate has a width d1Width d of bottom surface of concave plate2The relationship between them is:
d1＝d2＝H。
5. the sidewall face structure of claim 4, wherein the diameter of the cooling holes of the perforated plate is 1.5-2 mm, and the angle between the normal direction of the cooling holes and the normal direction of the perforated plate is 45-60 °.
6. The sidewall face structure of claim 5, wherein the structure is adapted for use in a mixed flow combustor having an angle α of less than 38 °.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011493571.5A CN112577069B (en) | 2020-12-17 | 2020-12-17 | Oblique flow combustion chamber side wall surface structure suitable for small head inclination angle |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202011493571.5A CN112577069B (en) | 2020-12-17 | 2020-12-17 | Oblique flow combustion chamber side wall surface structure suitable for small head inclination angle |
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| CN112577069A CN112577069A (en) | 2021-03-30 |
| CN112577069B true CN112577069B (en) | 2022-03-29 |
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| CN114777161A (en) * | 2022-04-11 | 2022-07-22 | 南京航空航天大学 | Inclined combustion chamber scheme for integrated design of coupling compressor and turbine |
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| CN100443806C (en) * | 2006-05-16 | 2008-12-17 | 北京航空航天大学 | Tangential standing vortex burning chamber |
| FR2917487B1 (en) * | 2007-06-14 | 2009-10-02 | Snecma Sa | TURBOMACHINE COMBUSTION CHAMBER WITH HELICOIDAL CIRCULATION OF THE AIR |
| FR2920523B1 (en) * | 2007-09-05 | 2009-12-18 | Snecma | TURBOMACHINE COMBUSTION CHAMBER WITH AIR HELICOIDAL CIRCULATION. |
| US20120324898A1 (en) * | 2011-06-21 | 2012-12-27 | Mcmahan Kevin Weston | Combustor assembly for use in a turbine engine and methods of assembling same |
| CN105953266B (en) * | 2016-05-04 | 2018-08-10 | 中国科学院工程热物理研究所 | A kind of oblique flow chamber structure |
| CN109654538B (en) * | 2018-12-07 | 2021-02-12 | 中国航发沈阳发动机研究所 | Venturi tube beneficial to reducing wall temperature of flame tube |
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