Aero-engine combustion chamber outlet sample gas sampler

Abstract

The invention belongs to the field of aero-engine combustion chamber outlet parameter measurement, and particularly relates to an aero-engine combustion chamber outlet sample gas sampler, which adopts a local impact cooling heat exchange structure, improves the temperature resistance of the windward side of the sampler, and can prolong the service life of the sampler in a combustion chamber outlet complex parameter measurement process. The flow of cooling water is greatly increased, and the cooling capacity of the whole structure is improved; and the mounting seat cavity is designed to cool the mounting seat, so that the possibility that the mounting seat is ablated in a high-temperature state is reduced.

Description

Technical Field

[0001] This application belongs to the field of measuring the outlet parameters of aero-engine combustors, and specifically relates to an outlet sampler for aero-engine combustors. Background Technology

[0002] As aero-engines develop towards higher temperatures and greater thrust, the demand for measuring combustion chamber exit parameters is increasing. The average temperature at the combustion chamber exit of advanced engines can reach 2000K, making traditional thermocouple and probe measurement methods inadequate for meeting the measurement requirements of combustion chamber exit parameters.

[0003] In recent years, gas analysis and measurement methods have been increasingly applied to the measurement of combustion chamber outlet parameters in aero-engines, and the technology has become largely mature. These methods utilize high-temperature, high-pressure resistant samplers to collect combustion chamber outlet gas samples. By analyzing the CO, CO2, NOx, and UHC (unburned hydrocarbons) in the sample gas, data on combustion chamber outlet temperature, pollutant emissions, and soot are obtained.

[0004] Current sample gas samplers used for analyzing and measuring combustion gases at the outlet parameters of aero-engine combustors have the following drawbacks:

[0005] Forced convection heat exchange cooling is adopted. Multiple baffles are arranged in the cavity to guide the circulation of cooling water. Due to the large number of baffles, the cooling water will generate a backflow zone at the large turning angle. The cooling water flow rate in the backflow zone is low, the heat exchange effect is poor, and it is easy to cause overheating and ablation. In addition, the mounting base lacks a cooling structure and is easily ablated and damaged, which can easily lead to the termination of the test and affect the test efficiency.

[0006] Due to size limitations, the diameter of the cooling water pipes inside the sampler is small, and the cooling water flow rate is relatively low, which cannot meet the overall cooling requirements. This results in poor local cooling, localized high temperatures, and a short service life.

[0007] Its internal structure is complex, and all materials are made of high-temperature alloys, making machining difficult and costly, and prone to problems such as bulging and deformation.

[0008] In view of the aforementioned technical deficiencies, this application is hereby filed. Summary of the Invention

[0009] The purpose of this application is to provide a sampler for the outlet gas of an aircraft engine combustion chamber to overcome or mitigate at least one of the known technical defects.

[0010] The technical solution of this application is:

[0011] A sampler for sample gas exiting the combustion chamber of an aero-engine includes a mounting base, a head, and a sampling tube;

[0012] The mounting base includes a mounting plate and a connecting rod vertically connected to the lower surface of the mounting plate;

[0013] The mounting base has a cooling water inlet chamber and a cooling water return chamber. The cooling water inlet chamber and the cooling water return chamber form openings on the upper surface of the mounting plate. There are two cooling water inlet chambers. The cooling water return chamber is located between the two cooling water inlet chambers.

[0014] The connecting rod sidewall is connected to a cooling water inlet pipe and a cooling water return pipe. There are two cooling water inlet pipes, which connect to two cooling water inlet chambers; the cooling water return pipe connects to the cooling water return chamber.

[0015] The head is attached to the top surface of the mounting plate at the bottom.

[0016] The head has a hollow structure with two baffles inside. The two baffles and the side walls on both sides of the head form a cooling guide cavity, and the two baffles form a cooling return cavity.

[0017] The two cooling guide chambers and the cooling return chamber are connected by an opening at the front of the head, and the two cooling guide chambers form an opening at the bottom of the head, which is connected to the opening formed by the two cooling water inlet chambers on the upper surface of the mounting plate; the cooling return chamber forms an opening at the bottom of the head, which is connected to the opening formed by the cooling water return chamber on the upper surface of the mounting plate.

[0018] Multiple guide plates are installed in the two cooling guide cavities. Each guide plate is connected to the water baffle plate and the head side wall on both sides. The front end extends to the connection between the cooling guide cavity and the cooling return cavity, and the rear end extends to the opening formed at the bottom of the head of the cooling guide cavity. The front end and the rear end are curved and transitioned.

[0019] The front of the head has a sampling hole, the front end of the sampling tube is connected to the sampling hole, and the rear end passes through the cooling return cavity and the cooling water return cavity and exits from the lower end of the connecting rod.

[0020] According to at least one embodiment of this application, in the above-mentioned sampler for the outlet gas of the aero-engine combustion chamber, the upper end of the connecting rod is a cylindrical section and the lower end is a flat plate section;

[0021] Two cooling water inlet pipes are connected to the lower end face of the cylindrical section and distributed on both sides of the flat section, while the cooling water return pipe is connected to the side wall of one side of the flat section.

[0022] According to at least one embodiment of this application, the above-mentioned sampler for the outlet gas of the aero-engine combustion chamber has multiple sampling tubes and their corresponding sampling holes.

[0023] According to at least one embodiment of this application, in the above-mentioned sampler for the outlet gas of the aero-engine combustion chamber, each sampling tube has the same diameter and is distributed at equal intervals or on equal annular surfaces.

[0024] According to at least one embodiment of this application, in the above-described sampler for the outlet gas of the aero-engine combustion chamber, each sampling hole is distributed along the vertical direction.

[0025] According to at least one embodiment of this application, in the above-mentioned sampler for the outlet gas of the aero-engine combustion chamber, the cooling water inlet pipe is a φ10 water pipe and the cooling water return pipe is a φ14 water pipe.

[0026] This application has at least the following beneficial technical effects:

[0027] Provides a sampler for the outlet gas of an aircraft engine combustion chamber:

[0028] The localized impact cooling heat exchange structure improves the temperature resistance of the sampler's windward side, which can extend the sampler's service life during the measurement of complex parameters at the combustion chamber outlet.

[0029] It significantly increased the cooling water flow rate and improved the overall cooling capacity of the structure;

[0030] The mounting base is designed with a cavity to cool it down and reduce the possibility of it being burned at high temperatures. Attached Figure Description

[0031] Figure 1 This is a three-dimensional view of the sampler for the outlet gas of the aero-engine combustion chamber provided in the embodiments of this application;

[0032] Figure 2 This is a front view of the sampler for the outlet gas of the aero-engine combustion chamber provided in the embodiments of this application;

[0033] Figure 3 yes Figure 2 Sectional view along direction E;

[0034] Figure 4 yes Figure 2 Sectional view along direction F;

[0035] Figure 5 This is a top-down view of the sampler for the outlet gas of an aero-engine combustion chamber provided in an embodiment of this application;

[0036] Figure 6 This is a side view of the sampler for the outlet gas of the aero-engine combustion chamber provided in the embodiments of this application;

[0037] Figure 7 yes Figure 6 Sectional view along line G;

[0038] Figure 8 yes Figure 6 H-direction sectional view;

[0039] in:

[0040] 1-Mounting base; 2-Head; 3-Cooling water inlet pipe; 4-Cooling water return pipe; 5-Water baffle; 6-Baffle plate; 7-Sampling pipe;

[0041] A-Cooling water inlet chamber;

[0042] B - Cooling return water chamber;

[0043] C-Cooling guide cavity;

[0044] D-Cooling Reflux Chamber.

[0045] To better illustrate this embodiment, some content in the accompanying drawings may be omitted, enlarged, or reduced. They are for illustrative purposes only and should not be construed as limiting the scope of this application. Detailed Implementation

[0046] To make the technical solution and advantages of this application clearer, the technical solution of this application will be described in a clearer and more complete manner below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are only some embodiments of this application, and are only used to explain this application, not to limit this application. It should be noted that, for ease of description, only the parts related to this application are shown in the accompanying drawings, and other related parts can be referred to the general design.

[0047] Furthermore, unless otherwise defined, the technical or scientific terms used in this application description shall have the ordinary meaning understood by one of ordinary skill in the art to which this application pertains. The word "comprising" as used in this application description indicates that the concept preceding the word encompasses the concepts listed following the word and their equivalents, without excluding other related concepts.

[0048] Furthermore, the terms indicating location used in the description of this application are only used to indicate relative directions or positional relationships. When the absolute position of the described object changes, its relative positional relationship may also change accordingly. It should also be noted that, unless otherwise explicitly specified and limited, terms such as "installation" and "connection" used in the description of this application should be interpreted broadly. For example, a connection can be a fixed connection or a detachable connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand its specific meaning in this application according to the specific circumstances.

[0049] A sampler for the exhaust gas from the combustion chamber of an aero-engine, such as Figures 1-8 As shown, it includes a mounting base 1, a head 2, and a sampling tube 7.

[0050] Mounting base 1 is T-shaped and includes a mounting plate and a connecting rod vertically connected to the lower surface of the mounting plate. The mounting plate is used to connect to the mounting groove opened inside the combustion chamber outlet measuring device, which can be connected by bolts. The connecting rod passes through the mounting port opened in the combustion chamber outlet measuring device.

[0051] The mounting base 1 has a cooling water inlet chamber A and a cooling water return chamber B. The cooling water inlet chamber A and the cooling water return chamber B form openings on the upper surface of the mounting plate. There are two cooling water inlet chambers A. The cooling water return chamber B is located between the two cooling water inlet chambers A and is in the middle of the mounting base 1.

[0052] The connecting rod sidewall is connected to cooling water inlet pipe 3 and cooling water return pipe 4. There are two cooling water inlet pipes 3, which connect to two cooling water inlet chambers A; the cooling water return pipe 4 connects to the cooling water return chamber B.

[0053] Specifically, the connecting rod can be designed with a cylindrical section at the top and a flat section at the bottom. Two cooling water inlet pipes 3 are connected to the lower end face of the cylindrical section and distributed on both sides of the flat section. The cooling water return pipe 4 is connected to the side wall of one side of the flat section.

[0054] The head 2 has a rectangular structure and its bottom is connected to the upper surface of the mounting plate. Specifically, the upper surface of the mounting plate can be designed to have a sliding groove with a front opening, and the bottom of the head 2 is flat, so that it slides into the sliding groove from the front opening for connection. Alternatively, the bottom of the head 2 can be designed to be integrally formed on the upper surface of the mounting plate.

[0055] The head 2 extends into the combustion chamber outlet. To reduce interference with the airflow at the combustion chamber outlet, the top, front windward side, and rear leeward side of the head 2 can be designed as arcs, with arc transitions between the corners.

[0056] The head 2 is a hollow structure with two baffles 5 inside. The two baffles 5 and the side walls on both sides of the head 2 form a cooling guide cavity C, and the two baffles 5 form a cooling return cavity D.

[0057] Two cooling guide chambers C and cooling return chamber D are connected by an opening at the front of the head 2. The two cooling guide chambers C form an opening at the bottom of the head 2, which is connected to the opening formed by the two cooling water inlet chambers A on the upper surface of the mounting plate. The cooling return chamber D forms an opening at the bottom of the head 2, which is connected to the opening formed by the cooling water return chamber B on the upper surface of the mounting plate. All of the openings can be designed as strips.

[0058] Multiple guide plates 6 are installed in the two cooling guide cavities C. Each guide plate 6 is connected to the water baffle plate 5 and the side wall of the head 2 on both sides. The front end extends to the connection between the cooling guide cavity C and the cooling return cavity D, and the rear end extends to the opening formed at the bottom of the head 2 of the cooling guide cavity C. The front end and the rear end are curved and transitioned.

[0059] The front windward side of the head 2 has a sampling hole, the front end of the sampling tube 7 is connected to the sampling hole, and the rear end passes through the cooling return cavity D and the cooling return water cavity B and exits from the lower end of the connecting rod.

[0060] When the sampler for the exhaust gas at the combustion chamber outlet of the aircraft engine disclosed in the above embodiment is sampling the sample gas, the front windward side of the head 2 faces the exhaust gas flow at the combustion chamber outlet, so that the exhaust gas flow at the combustion chamber outlet can enter the sampling tube 7 through the sampling hole, be led out from the sampling tube 7, and be collected to complete the exhaust gas sampling for subsequent analysis.

[0061] During the sample gas sampling process, cooling water can be introduced into the cooling water inlet chamber A through the cooling water inlet pipe 3. After the cooling water is rectified and stabilized in the cooling water inlet chamber A, it flows evenly into the cooling guide chamber C, and then flows evenly out of the cooling guide chamber C along the guide plate 6, providing efficient impact cooling to the front windward surface of the head 2, which is most severely heated. Afterward, it flows out through the cooling return chamber D, the cooling return water chamber B, and the cooling return water pipe 4, which can cool the mounting base 1 and the head 2 along the way to prevent overheating and burning.

[0062] Multiple sampling tubes 7 and their corresponding sampling holes can be designed as needed. Each sampling tube 7 has the same diameter and is distributed at equal intervals or on equal annular surfaces. Each sampling hole can be distributed along the vertical direction.

[0063] Cooling water inlet pipe 3 is a φ10 water pipe, and cooling water return pipe 4 is a φ14 water pipe. The cross-sectional area of ​​the pipes has been increased by 8 times, which can meet the flow of more cooling water and improve the overall cooling capacity.

[0064] The baffle plate 6 in the cooling guide cavity C serves two purposes. First, it strengthens the structure by connecting the side wall of the head 2 to the baffle plate 5, preventing bulging caused by excessive internal and external pressure difference. Second, it straightens the flow, making the cooling water flow more uniform, preventing backflow zones, and ensuring the cooling effect on the windward side of the head 2.

[0065] The sampler for the outlet gas of the aero-engine combustion chamber disclosed in the above embodiments adopts a heat transfer method of convection heat transfer plus local impingement cooling, and increases the cooling water flow area to improve the cooling heat transfer capacity.

[0066] The cooling water flows evenly along the guide plate 6 in the cooling guide cavity C to the heat-concentrated part of the front windward side of the head 2, and performs cooling and heat exchange in the form of impact cooling. This can avoid the backflow zone affecting the heat exchange effect. After the impact heat exchange is completed, it flows back through the cooling backflow cavity D to complete the heat exchange. This can effectively improve the heat exchange and cooling effect on the heat-concentrated part of the head 2, and can improve the service life of the gas analyzer in the high temperature and high pressure environment at the outlet of the aero-engine combustion chamber.

[0067] The mounting base 1 is designed with a cavity structure, making full use of the remaining space of the mounting base 1 and increasing the inlet and outlet water flow area by 8 times. This can effectively increase the cooling water flow rate, improve the overall heat exchange capacity of the sampler, meet the cooling water's heat exchange requirements for the mounting base 1, reduce the possibility of the mounting base 1 being burned at high temperatures, enhance the high temperature resistance, avoid the problem of the sampler failing during the test and causing the test to be stopped, and improve the test efficiency.

[0068] The structure is relatively simple, using only two baffles 5 and guide plates 6 to control the flow of cooling water. The machining is relatively simple, which can reduce the processing cost.

[0069] The technical solution of this application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of this application is obviously not limited to these specific embodiments. Without departing from the principles of this application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will all fall within the scope of protection of this application.

Claims

1. A sampler for the outlet gas of an aero-engine combustion chamber, characterized in that, Includes mounting base (1), head (2), and sampling tube (7); The mounting base (1) includes a mounting plate and a connecting rod vertically connected to the lower surface of the mounting plate; The mounting base (1) has a cooling water inlet chamber (A) and a cooling water return chamber (B). The cooling water inlet chamber (A) and the cooling water return chamber (B) form openings on the upper surface of the mounting plate. There are two cooling water inlet chambers (A). The cooling water return chamber (B) is located between the two cooling water inlet chambers (A). The connecting rod sidewall is connected to the cooling water inlet pipe (3) and the cooling water return pipe (4). There are two cooling water inlet pipes (3), which connect to the two cooling water inlet chambers (A); the cooling water return pipe (4) connects to the cooling water return chamber (B). The head (2) is attached to the top surface of the mounting plate; The head (2) is a hollow structure with two baffles (5) inside. The two baffles (5) and the side walls on both sides of the head (2) form a cooling guide cavity (C), and the two baffles (5) form a cooling return cavity (D). Two cooling guide chambers (C) and cooling return chamber (D) are connected by an opening at the front of the head (2), and the two cooling guide chambers (C) form an opening at the bottom of the head (2), which is connected to the opening formed by the two cooling water inlet chambers (A) on the upper surface of the mounting plate; the cooling return chamber (D) forms an opening at the bottom of the head (2), which is connected to the opening formed by the cooling water return chamber (B) on the upper surface of the mounting plate; Multiple guide plates (6) are installed in the two cooling guide chambers (C). Each guide plate (6) is connected to the water baffle (5) and the side wall of the head (2) on both sides. The front end extends to the connection between the cooling guide chamber (C) and the cooling return chamber (D), and the rear end extends to the opening formed at the bottom of the head (2) of the cooling guide chamber (C). The front end and the rear end are curved and transitioned. The front windward side of the head (2) has a sampling hole, the front end of the sampling tube (7) is connected to the sampling hole, and the rear end passes through the cooling return cavity (D) and the cooling return water cavity (B) and exits from the lower end of the connecting rod.

2. The sampler for the outlet gas of the aero-engine combustion chamber according to claim 1, characterized in that, The upper end of the connecting rod is a cylindrical section, and the lower end is a flat plate section; Two cooling water inlet pipes (3) are connected to the lower end face of the cylindrical section and distributed on both sides of the flat section. The cooling water return pipe (4) is connected to the side wall of one side of the flat section.

3. The sampler for the outlet gas of the aero-engine combustion chamber according to claim 2, characterized in that, There are multiple sampling tubes (7) and their corresponding sampling holes.

4. The sampler for the outlet gas of the aero-engine combustion chamber according to claim 3, characterized in that, Each sampling tube (7) has the same diameter and is distributed at equal intervals or on equal annular surfaces.

5. The sampler for the outlet gas of the aero-engine combustion chamber according to claim 3, characterized in that, Each sampling hole is distributed along the vertical direction.

6. The sampler for the outlet gas of the aero-engine combustion chamber according to claim 5, characterized in that, The cooling water inlet pipe (3) is a φ10 water pipe, and the cooling water return pipe (4) is a φ14 water pipe.

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