阅读说明：本技术 一种燃气轮机引射器 (Gas turbine ejector ) 是由 郑登强 安旭松 马关田 冯德润 于 2021-09-18 设计创作，主要内容包括：一种燃气轮机引射器,包括外壳体、中壳体、内壳体、以及粉剂进料管；外壳体的右端设置有用于连接燃气轮机的进气口；所述中壳体设置在所述外壳体的内部,所述中壳体与所述外壳体之间存在间隙形成燃气轮机尾气副流道；所述内壳体设置在所述中壳体的内部,中壳体的右端部与内壳体的右端相连接；所述中壳体与内壳体之间存在间隙形成粉剂引射流道；所述粉剂进料管穿过所述外壳体和中壳体与粉剂引射流道连通；所述内壳体上设置有燃气轮机尾气主流道。燃气轮机高速射流尾气进入引射器后分两路,一路经过燃气轮机尾气主流道,一路经过燃气轮机尾气副流道,通过对燃气轮机高速射流尾气分路,避免燃气轮机高速射流尾气封堵憋压,对燃气轮机造成反压影响。(A gas turbine ejector comprises an outer shell, a middle shell, an inner shell and a powder feeding pipe; the right end of the outer shell is provided with an air inlet used for connecting a gas turbine; the middle shell is arranged inside the outer shell, and a gap is formed between the middle shell and the outer shell to form a gas turbine tail gas auxiliary runner; the inner shell is arranged inside the middle shell, and the right end part of the middle shell is connected with the right end of the inner shell; a gap is formed between the middle shell and the inner shell to form a powder injection flow passage; the powder feeding pipe penetrates through the outer shell and the middle shell and is communicated with the powder injection flow passage; the inner shell is provided with a gas turbine tail gas main runner. The high-speed jet tail gas of the gas turbine enters the ejector and then is divided into two paths, wherein one path of the high-speed jet tail gas passes through a tail gas main flow channel of the gas turbine, the other path of the high-speed jet tail gas passes through a tail gas auxiliary flow channel of the gas turbine, and the high-speed jet tail gas of the gas turbine is divided into paths, so that the high-speed jet tail gas plugging of the gas turbine is prevented from suppressing pressure and the back pressure influence on the gas turbine is avoided.)

1. A gas turbine ejector, comprising: an outer shell (10), a middle shell (20), an inner shell (30) and a powder feeding pipe (80);

the right end of the outer shell (10) is provided with an air inlet (105) used for connecting a gas turbine;

the middle shell (20) is arranged inside the outer shell (10), and a gap is formed between the middle shell (20) and the outer shell (10) to form a gas turbine tail gas secondary flow passage (50);

the inner shell (30) is arranged inside the middle shell (20), and the right end part of the middle shell (20) is connected with the right end of the inner shell (30); a gap is formed between the middle shell (20) and the inner shell (30) to form a powder injection flow passage (70); the powder feeding pipe (80) penetrates through the outer shell (10) and the middle shell (20) and is communicated with the powder injection flow passage (70);

the inner shell (30) is provided with a gas turbine tail gas main flow passage (60).

2. The gas turbine ejector of claim 1, wherein: the outer shell (10), the middle shell (20) and the inner shell (30) are connected through a connecting rod (40).

3. The gas turbine ejector of claim 1, wherein: the inner shell (30) comprises an inner shell straight cylinder part (302) and an inner shell convergence part (301) arranged at the left end of the inner shell straight cylinder part (302); the inner shell convergence part (301) is of a conical shell structure, and the section diameter of the inner shell convergence part (301) is gradually reduced from right to left.

4. The gas turbine ejector of claim 3, wherein: the middle shell (20) comprises a middle shell straight cylinder part (203), a middle shell left cone part (202) arranged at the left end of the middle shell straight cylinder part (203), and a middle shell right cone part (204) arranged at the right end of the middle shell straight cylinder part (203);

gaps between the inner shell convergence part (301) and the middle shell left cone part (202) and gaps between the inner shell straight cylinder part (302) and the middle shell straight cylinder part (203) are equal; the right end of the middle shell right conical part (204) is connected with the right end of the inner shell straight cylinder part (302).

5. The gas turbine ejector of claim 4, wherein: the outer shell (10) comprises an outer shell straight cylinder part (102), an outer shell left cone part (101) arranged at the left end of the outer shell straight cylinder part (102), and an outer shell right cone part (103) arranged at the right end of the outer shell straight cylinder part (102);

gaps between the outer shell left tapered part (101) and the middle shell left tapered part (202), between the outer shell straight tube part (102) and the middle shell straight tube part (203), and between the outer shell right tapered part (103) and the middle shell right tapered part (204) are equal.

6. The gas turbine ejector of claim 5, wherein: the middle shell (20) further comprises an exhaust ring (201) arranged at the left end of the middle shell left conical part (202), and the left end face of the exhaust ring (201) extends out of the shell left conical part (101).

7. The gas turbine ejector of claim 5, wherein: the outer shell (10) further comprises an air inlet ring (104) arranged at the right end of the right conical part (103) of the outer shell.

8. The gas turbine ejector of claim 7, wherein: and a fixing ring is arranged at the right end of the air inlet ring (104).

9. The gas turbine ejector of claim 2, wherein: the number of the connecting rods (40) is at least four, and the connecting rods are uniformly distributed on the same circumferential surface.

10. The gas turbine ejector of claim 1, wherein: the powder feeding pipe (80) is obliquely arranged, and the feeding end of the powder feeding pipe is inclined towards the air inlet end.

Technical Field

The invention relates to the technical field of fuming vehicles, in particular to a gas turbine ejector for a fuming vehicle.

Background

The gas turbine ejector is an accessory of a smoke generating vehicle for a smoke generating army and is mainly used for providing partial power and a flow channel for the smoke generating vehicle to generate infrared interference smoke curtains. The smoke generating vehicle can provide smoke screens and interference environments for relevant actual combat drilling of army, increase actual combat drilling projects, simulate actual combat scenes, and enrich the operation experience of operators under the smoke screens and the interference environments.

The gas turbine ejector is used for being matched with a small-sized gas turbine. However, the existing gas turbine ejector has air resistance to ejected airflow, the ejection speed is low, and high-speed jet tail gas plugging and pressure holding of the gas turbine are easily caused, so that back pressure influence is caused on the gas turbine.

Disclosure of Invention

The invention mainly aims to provide a gas turbine ejector, and aims to solve the technical problem.

In order to achieve the above object, the present invention provides an injector of a gas turbine, comprising: the device comprises an outer shell, a middle shell, an inner shell and a powder feeding pipe; the right end of the outer shell is provided with an air inlet used for connecting a gas turbine; the middle shell is arranged inside the outer shell, and a gap is formed between the middle shell and the outer shell to form a gas turbine tail gas auxiliary runner; the inner shell is arranged inside the middle shell, and the right end part of the middle shell is connected with the right end of the inner shell; a gap is formed between the middle shell and the inner shell to form a powder injection flow passage; the powder feeding pipe penetrates through the outer shell and the middle shell and is communicated with the powder injection flow passage; the inner shell is provided with a gas turbine tail gas main runner.

Preferably, the outer shell, the middle shell and the inner shell are connected through a connecting rod.

Preferably, the inner shell comprises an inner shell straight cylinder part and an inner shell convergence part arranged at the left end of the inner shell straight cylinder part; the inner shell convergence part is of a conical shell structure, and the diameter of the section of the inner shell convergence part is gradually reduced from right to left.

Preferably, the middle shell comprises a middle shell straight cylinder part, a middle shell left cone part arranged at the left end of the middle shell straight cylinder part and a middle shell right cone part arranged at the right end of the middle shell straight cylinder part; gaps between the inner shell convergence part and the middle shell left conical part and gaps between the inner shell straight cylinder part and the middle shell straight cylinder part are equal; the right end of the right cone part of the middle shell is connected with the right end of the straight cylinder part of the inner shell.

Preferably, the outer shell comprises an outer shell straight cylinder part, an outer shell left cone part arranged at the left end of the outer shell straight cylinder part, and an outer shell right cone part arranged at the right end of the outer shell straight cylinder part; gaps between the outer shell left cone part and the middle shell left cone part, between the outer shell straight cylinder part and the middle shell straight cylinder part and between the outer shell right cone part and the middle shell right cone part are equal.

Preferably, the middle shell further comprises an exhaust ring arranged at the left end of the left conical part of the middle shell, and the left end surface of the exhaust ring extends out of the left conical part of the outer shell.

Preferably, the outer shell further comprises an air inlet ring arranged at the right end of the right conical part of the outer shell.

Preferably, a fixing ring is provided at a right end of the air inlet ring.

Preferably, the number of the connecting rods is at least four, and the connecting rods are uniformly distributed on the same circumferential surface.

Preferably, the powder inlet pipe sets up for the slope, and its feed end inclines to the inlet end for the powder inlet pipe draws the flue powder antegrade powder that penetrates to draw the export direction of penetrating the runner, and the flue powder spills in the air along with high-speed efflux gas more easily, forms effective interference smoke.

The invention achieves the following beneficial effects:

(1) the high-speed jet tail gas of the gas turbine enters the ejector and then is divided into two paths, wherein one path of the high-speed jet tail gas passes through a tail gas main flow channel of the gas turbine, the other path of the high-speed jet tail gas passes through a tail gas auxiliary flow channel of the gas turbine, and the high-speed jet tail gas of the gas turbine is divided into paths, so that the high-speed jet tail gas plugging of the gas turbine is prevented from suppressing pressure and the back pressure influence on the gas turbine is avoided. The powder is sprayed into the powder injection flow channel through the powder feeding pipe, kinetic energy is obtained under the injection effect of high-speed jet gas in the main flow channel of the tail gas of the gas turbine, and the kinetic energy is distributed into the air along with the high-speed jet gas to form an effective interference smoke screen.

(2) Compared with the traditional gas turbine ejector, the invention does not need to eject air, so the invention is smaller and lighter in volume and mass and has more compact structure compared with the traditional gas turbine ejector.

(3) The gas turbine ejector provided by the invention adopts a multilayer structure consisting of the outer shell, the middle shell and the inner shell, and forms a gas turbine tail gas secondary flow passage, a powder ejection flow passage and a gas turbine tail gas main flow passage, the gas resistance is small, each flow passage cannot obstruct the ejection of powder, and the powder ejection quantity and the ejection speed are improved.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the structures shown in the drawings without creative efforts.

FIG. 1 is a schematic diagram of an injector for a gas turbine according to the present invention;

FIG. 2 is a schematic diagram of the high velocity jet tail gas and dust circuit of a gas turbine according to the present invention;

description of reference numerals: 10-an outer shell; 101-casing left cone; 102-a housing straight section; 103-right cone of housing; 104-an air inlet ring; 105-an air inlet; 20-a middle shell; 201-an exhaust ring; 202-middle shell left cone; 203-middle shell straight cylinder part; 204-right cone of middle shell; 30-an inner housing; 301-inner shell straight section; 302-inner shell convergence; 40-a connecting rod; 50-a gas turbine tail gas secondary runner; 60-a main gas turbine tail gas channel; 70-powder injection flow channel; 80-powder feeding pipe.

Detailed Description

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

It should be noted that all the directional indicators (such as up, down, left, right, front, and rear … …) in the embodiment of the present invention are only used to explain the relative position relationship between the components, the movement situation, etc. in a specific posture (as shown in the drawing), and if the specific posture is changed, the directional indicator is changed accordingly.

As shown in fig. 1, an embodiment of a gas turbine ejector structure provided by the present invention is a gas turbine ejector, including: an outer housing 10, a middle housing 20, an inner housing 30, and a powder feeding tube 80; the right end of the outer shell 10 is provided with an air inlet 105 for connecting a gas turbine; the middle shell 20 is arranged inside the outer shell 10, and a gap exists between the middle shell 20 and the outer shell 10 to form a gas turbine exhaust secondary runner 50; the inner housing 30 is arranged inside the middle housing 20, and the right end part of the middle housing 20 is connected with the right end of the inner housing 30; a gap is formed between the middle shell 20 and the inner shell 30 to form a powder injection flow passage 70; the powder feeding pipe 80 passes through the outer shell 10 and the middle shell 20 to be communicated with the powder injection flow passage 70; the inner casing 30 is provided with a gas turbine exhaust main flow passage 60.

In the present embodiment, the outer housing 10, the middle housing 20, and the inner housing 30 are connected by a connecting rod 40. Specifically, the number of the connecting rods 40 is at least four, and the connecting rods are uniformly distributed on the same circumferential surface.

In the present embodiment, the inner casing 30 is a hollow casing structure with two open ends to form a main flow passage 60 of the gas turbine exhaust. Specifically, the inner housing 30 includes an inner housing straight-tube portion 302, and an inner housing converging portion 301 provided at the left end of the inner housing straight-tube portion 302; the inner shell convergence portion 301 is a conical shell structure, and the cross-sectional diameter of the inner shell convergence portion 301 is gradually reduced from right to left. After the inner shell 30 is converged by the inner shell convergence portion 301, the air flow velocity is increased, which is helpful for enhancing the injection.

In this embodiment, the middle case 20 includes a middle case straight tube portion 203, a middle case left pyramid part 202 provided at the left end of the middle case straight tube portion 203, and a middle case right pyramid part 204 provided at the right end of the middle case straight tube portion 203, and the right end of the middle case right pyramid part 204 is connected to the right end of the inner case straight tube portion 302. The right cone portion 204 of the middle casing forms a flow guiding cone surface to facilitate the entry of the high-speed jet exhaust gas of the gas turbine into the exhaust gas secondary channel 50 of the gas turbine.

Further, the gaps between the inner shell convergence part 301 and the middle shell left cone part 202 and between the inner shell straight cylinder part 302 and the middle shell straight cylinder part 203 are equal, that is, the powder injection flow passage 70 has an equal-gap structure, so that the powder can be stably injected.

In the present embodiment, the outer case 10 includes an outer case straight tube portion 102, an outer case left tapered portion 101 provided at the left end of the outer case straight tube portion 102, and an outer case right tapered portion 103 provided at the right end of the outer case straight tube portion 102. Gaps between the casing left tapered portion 101 and the middle casing left tapered portion 202, between the casing straight tube portion 102 and the middle casing straight tube portion 203, and between the casing right tapered portion 103 and the middle casing right tapered portion 204 are equal. That is, the whole gas turbine tail gas auxiliary flow passage 50 is of an equal-gap structure, and the distances between the normal directions of all parts of the gas turbine tail gas auxiliary flow passage 50 are equal, so that tail gas in the gas turbine tail gas auxiliary flow passage 50 can be stably sprayed.

In the present embodiment, the middle shell 20 further includes an exhaust ring 201 disposed at the left end of the middle shell left cone 202, and the left end surface of the exhaust ring 201 extends out of the outer shell left cone 101. Through setting up the exhaust ring 201 structure, can avoid gas turbine tail gas auxiliary flow channel 50's air current to draw to penetrate runner 70 and cause the interference to the powder, guarantee that the powder is smoothly drawn out of penetrating, exhaust ring 201 can also make the axis direction blowout along the ejector of gas turbine tail gas main flow channel 60 simultaneously, further guarantees the injection direction who disturbs the smoke screen.

In this embodiment, the outer casing 10 further includes an air inlet ring 104 disposed at the right end of the right tapered part 103 of the outer casing, and the inner hole of the air inlet ring 104 forms the air inlet 105. The right end of the air inlet ring 104 is provided with a fixing ring which is in a flange edge structure and is used for being connected with the gas turbine so as to be convenient for installation and connection. Through setting up air inlet ring 104, can also make the direction of admitting air and ejector axial parallel, be favorable to gas turbine high-speed efflux tail gas smoothly to get into in the ejector.

In this embodiment, the powder feed tube 80 is inclined with its feed end inclined toward the gas inlet end. This structure can make the flue powder that powder inlet pipe 80 penetrated the entering draw the export direction that runner 70 was drawn to the powder cisoid powder, and the flue powder spills the air along with high-speed efflux gas distribution more easily, forms effective interference smoke.

The high-speed jet tail gas and powder agent route of the gas turbine is shown in figure 2, wherein the route A is a main high-speed jet tail gas route of the gas turbine, the route B is a powder agent route, and the route C is a high-speed jet tail gas auxiliary route of the gas turbine. The specific working principle of the invention is as follows: the high-speed jet tail gas of the gas turbine enters the ejector and then is divided into two paths, one path passes through a main tail gas flow passage 60 (a path in fig. 2) of the gas turbine, the other path passes through a secondary tail gas flow passage 50 (C path in fig. 2) of the gas turbine, and the high-speed jet tail gas of the gas turbine is shunted, so that the blocking and the pressure holding of the high-speed jet tail gas of the gas turbine are avoided, and the back pressure influence on the gas turbine is caused. The powder is injected into the powder injection flow passage 70 through the powder feeding pipe 80, obtains kinetic energy under the injection action of the high-speed jet gas in the gas turbine tail gas main flow passage 50, and is distributed into the air along with the high-speed jet gas (route B in fig. 2), so as to form an effective interference smoke screen.

The above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention, and all modifications and equivalents of the present invention, which are made by the contents of the present specification and the accompanying drawings, or directly/indirectly applied to other related technical fields, are included in the scope of the present invention.