Titanium fire containment test device and test method

Abstract

The invention provides a titanium fire containment test device and a titanium fire containment test method, which are used for testing the titanium fire containment capacity of a gas compressor casing, and the titanium fire test device comprises a first test shell, a second test shell, a test blade and an ignition piece, wherein the first test shell and the second test shell are enclosed to form a test cavity, and test airflow is introduced into the test cavity; the test blade is arranged in the test cavity; the ignition piece is located on a flowing path of the test airflow; the ignition piece can generate a high-temperature product after being ignited, and then the high-temperature product impacts the first test shell, the second test shell and the test blade under the action of the test airflow. The titanium fire containment test device can be used for testing the titanium fire prevention performance of the compressor casing.

Description

Technical Field

[0001] This invention relates to the field of compressor technology, and in particular to a titanium fire containment test apparatus and test method. Background Technology

[0002] Advanced aero engines, both domestically and internationally, widely utilize titanium alloys as materials for components such as compressor casings, blades, bladed disks, fan ducts, and combustion chamber shells in their compressors (high-pressure compressors and booster stages). However, titanium alloys have low thermal conductivity and high calorific value, posing a fatal challenge of sustained combustion sensitivity, which can lead to titanium fire malfunctions. Since the application of titanium alloys in aero engines, titanium fire accidents have occurred repeatedly. These fires often occur within the high-pressure compressor, burning not only titanium alloy blades within seconds but also damaging non-titanium alloy materials such as casings, bladed disks, and shafts, resulting in catastrophic crashes and loss of life.

[0003] Studies have shown that when the airflow within a high-pressure compressor meets certain velocity, temperature, and pressure conditions, titanium fires are easily generated when the high-speed rotating titanium rotor blades collide and rub against the casing or external objects. According to CCAR 33.17's fire protection requirements for aero engines and FAA Advisory Circular AC33-4's principles for the design and use of titanium materials, the titanium fire protection requirements for compressor casings are as follows: The design, construction, and materials used in the compressor casing must accommodate potential fires and subsequent damage, thus complying with FAR 33.17(a) and 33.19. The compressor casing cannot be made of titanium in areas where titanium fires may occur unless the casing is adequately protected to contain the fire and its subsequent damage. Currently, various titanium fire testing devices, such as friction ignition, laser ignition, and droplet ignition, have been developed to address different fire causes.

[0004] However, existing titanium fire testing equipment focuses on the ignition characteristics of titanium materials themselves. To test the titanium fire containment, a real engine platform must be used to verify the titanium fire containment, which results in excessively high test cycles and costs. Summary of the Invention

[0005] The purpose of this invention is to provide a titanium fire containment test device and test method, which can test the titanium fire resistance of compressor casing.

[0006] One aspect of the present invention provides a titanium fire containment testing device for testing the titanium fire containment capability of a compressor casing. The titanium fire testing device includes a first test housing, a second test housing, a test blade, and an ignition element. The first and second test housings enclose a test chamber, through which a test airflow passes. The test blade is disposed within the test chamber. The ignition element is located in the flow path of the test airflow. Upon ignition, the ignition element generates high-temperature products, which, under the action of the test airflow, impact the first test housing, the second test housing, and the test blade.

[0007] In one embodiment, the titanium fire containment test apparatus further includes an air intake structure; the air intake structure has an air intake channel; the air intake structure is connected to the first test housing and the second test housing, and the air intake channel is connected to the test chamber so that the test airflow can enter the test chamber from the air intake channel.

[0008] In one embodiment, the angle between the central axis of the air intake channel and the central axis of the test chamber ranges from 15° to 65°.

[0009] In one embodiment, the air intake structure has a laser incident window, which is provided with germanium glass; and / or the air intake structure has an observation window, which is provided with transmission glass.

[0010] In one embodiment, the titanium fire containment test apparatus further includes a rocker arm; the test blade includes a rotating shaft and a blade body connected to the rotating shaft, the blade body being located within the test chamber; the rotating shaft of the test blade passes through the first test housing and is connected to the rocker arm, and the rotation of the rocker arm thereby drives the blade body of the test blade to rotate.

[0011] In one embodiment, the titanium fire containment test apparatus further includes a rotating base; the rotating base is detachably connected to the first test housing; one end of the rocker arm is fixedly connected to the rotating shaft of the test blade, and the other end of the rocker arm is fixedly connected to the rotating base; the position of the rotating base relative to the first test housing changes, thereby causing the circumferential angle of the blade body of the test blade to change.

[0012] In one embodiment, the first test housing is provided with a plurality of connection holes for connecting with the air intake structure; the rotating base and at least one of the connection holes of the first test housing are detachably connected.

[0013] In one embodiment, the ignition element includes a fixed portion and an ignition portion connected to the fixed portion; the fixed portion of the ignition element is connected to the first test housing; the ignition portion of the ignition element is located within the air intake channel of the air intake structure and is located upstream of the first test housing, the second test housing, and the test blade in the flow path of the test airflow.

[0014] In one embodiment, the ignition element further includes an extension connected to the fixing portion; the ignition portion is obliquely disposed on the extension.

[0015] In one embodiment, the first test housing is provided with a plurality of connection holes for connection with the air intake structure; the fixing portion of the igniter is detachably connected to at least one of the connection holes of the first test housing.

[0016] In one embodiment, the number of test blades is multiple, and they are spaced apart within the test chamber.

[0017] In one embodiment, the number of ignition elements is matched with the number of test blades.

[0018] In one embodiment, the ignition element is ignited by flame impact or by plasma arc.

[0019] In one embodiment, the ignition element is made of the same material as the titanium alloy rotor blade model of the compressor.

[0020] In one embodiment, the test blade is made of titanium alloy or alloy steel.

[0021] In one embodiment, the surface of the test blade, made of titanium alloy, is coated with a flame-retardant coating.

[0022] Another aspect of the present invention provides a titanium fire containment test method, applied to the titanium fire containment test apparatus as described in any of the above embodiments; the titanium fire containment test method includes: introducing test gas into the test chamber and igniting the ignition element; capturing the combustion state of the first test housing, the second test housing, and the test blade using a camera device; stopping the introduction of the test gas flow and disassembling the cooled ignition element, the first test housing, the second test housing, and the test blade; and analyzing the ablation condition of the ignition element, the first test housing, the second test housing, and the test blade.

[0023] The titanium fire containment test device of the present invention addresses the question of whether titanium fire in compressor titanium alloy rotor blades will burn through the casing. It models the titanium alloy rotor blades as ignition elements, and uses a first test shell and a second test shell to simulate the compressor casing and test blades to simulate stator blades. The ignition elements are ignited to simulate the titanium fire process, thereby verifying whether the fire resistance performance of the compressor casing can meet the requirements for titanium fire prevention. The device is simple in configuration, compact in structure, and has a low test cycle and low cost. Attached Figure Description

[0024] The above and other features, properties and advantages of the present invention will become more apparent from the following description taken in conjunction with the accompanying drawings and embodiments, wherein:

[0025] Figure 1 This is a schematic diagram of an embodiment of the titanium fire containment test apparatus according to the present invention;

[0026] Figure 2 yes Figure 1 A schematic diagram of the test structure of the titanium fire containment test apparatus;

[0027] Figure 3 yes Figure 2 The diagram shows the structural assembly relationship.

[0028] Figure 4 yes Figure 1 Top view of the titanium fire containment test apparatus;

[0029] Figure 5 yes Figure 1 A schematic diagram of the air intake structure of the titanium fire containment test device.

[0030] Figure 6 yes Figure 1 A schematic diagram of the structure of the first test shell of the titanium fire containment test apparatus in one embodiment;

[0031] Figure 7 yes Figure 6 AA section view in the middle;

[0032] Figure 8 yes Figure 1 A schematic diagram of another embodiment of the first test shell and the second test shell of the titanium fire containment test device;

[0033] Figure 9 This is a diagram of the compressor's meridional structure;

[0034] Figure 10 yes Figure 1 Enlarged view of the ignition element of the titanium fire containment test apparatus;

[0035] Figure 11 yes Figure 1A schematic diagram of one embodiment of the ignition element shown;

[0036] Figure 12 yes Figure 1 A schematic diagram of another embodiment of the ignition element shown;

[0037] Figure 13 yes Figure 1 A schematic diagram of another embodiment of the ignition element shown;

[0038] Figure 14 This is a schematic diagram of the test structure of another embodiment of the titanium fire containment test apparatus according to the present invention;

[0039] Figure 15 This is a schematic flowchart of an embodiment of the titanium fire containment test method according to the present invention. Detailed Implementation

[0040] Reference will now be made in detail to embodiments of the invention, one or more examples of which are illustrated in the accompanying drawings. Each example is provided to explain the invention and not to limit it. In fact, it will be apparent to those skilled in the art that various modifications and variations may be made to the invention without departing from the scope or spirit thereof. For example, a feature shown or described as part of one embodiment may be used with another embodiment to produce yet another embodiment. Therefore, the invention is intended to cover these modifications and variations that fall within the scope of the appended claims and their equivalents.

[0041] As used herein, the term "axial" refers to the central axis of the structure or a direction parallel to the central axis of the structure; the term "radial" refers to a direction perpendicular to the "axial" direction; and the term "circumferential" refers to a direction about the "axial" direction. The terms "first" and "second" are used interchangeably to distinguish one component from another and are not intended to indicate the location or importance of individual components. The terms "upstream" and "downstream" refer to the relative directions of the test gas flow within the flow path. For example, "upstream" refers to the direction from which the test gas flows, and "downstream" refers to the direction towards which the test gas flows.

[0042] The term "titanium fire" refers to the phenomenon where titanium or titanium alloy components ignite and burn due to factors such as severe impact or friction, causing damage or destruction. Titanium alloys are widely used in the compressor structure (high-pressure compressor and booster stage) of civil aircraft engines, and these alloys can ignite and burn under severe impact or friction, causing damage or destruction. A titanium fire can range from minor tip and trailing-edge combustion to widespread burning, not only destroying all titanium alloy blades but also damaging other non-titanium alloy parts such as the casing, fairing blades, bladed disks, and shafts. It can even cause varying degrees of damage to the combustion chamber flame tube and turbine blades.

[0043] Figure 1 and Figure 2 The structure of one embodiment of the titanium fire containment testing device of the present invention is shown. The titanium fire containment testing device of the present invention addresses the need for titanium fire containment verification of aero-engine compressors, specifically targeting the question of whether the compressor casing will burn through after a titanium fire occurs in the titanium alloy rotor blades of the compressor, that is, verifying the titanium fire resistance capability of the compressor casing.

[0044] The titanium fire containment testing apparatus of the present invention is used to test the titanium fire containment capability of a compressor casing. The titanium fire testing apparatus includes a first test housing 100, a second test housing 200, a test blade 300, and an ignition element 400. The first test housing 100, the second test housing 200, the test blade 300, and the ignition element 400 constitute the test structure of the present invention. Figure 2 As shown, the first test housing 100 and the second test housing 200 enclose to form a test chamber 10. The first test housing 100 and the second test housing 200 are connected, forming a single test housing unit used to simulate a compressor casing. Figure 1 In the vertical direction shown, the first test housing 100 is located above the second test housing 200. The test chamber 10 is filled with test airflow, which is used to simulate the real environment of a compressor.

[0045] Test blades 300 are installed inside the test chamber 10. For example, Figure 2 As shown, the blade body 310 of the test blade 300 is located inside the test chamber 10. In this way, the test blade 300 can be located within the test airflow flowing inside the test chamber 10, which can better simulate the real operating conditions of the compressor.

[0046] The ignition element 400 is located on the flow path of the test gas flow. The flow path of the test gas flow refers to the trajectory of the test gas flow within the test chamber 10. The characteristics of the flow path of the test gas flow depend on its properties, the properties of the test chamber 10, and other conditions. Figure 1 and Figure 2 The flow path of the test airflow is Figure 1 The direction of the trajectory from left to right, that is, from Figure 1 as well as Figure 2 The direction from the first end 110 of the first test housing 100 to the second end 120 of the first test housing 100 (or the direction from the first end 210 of the second test housing 200 to the second end 220 of the second test housing 200).

[0047] The experimental airflow in this invention is a high-temperature, high-pressure, and high-speed airflow, which can effectively simulate the high-temperature, high-pressure, and high-speed airflow environment when titanium fire is generated inside the compressor.

[0048] The test airflow can be generated by an air source (not shown), and the mainstream velocity, temperature, and pressure of the generated test airflow inside the compressor can be precisely controlled to simulate the real working conditions of the compressor.

[0049] The ignition element 400 generates high-temperature products upon ignition, which then impact the first test housing 100, the second test housing 200, and the test blade 300 under the influence of the test airflow. Considering that in actual high-pressure compressor operation, titanium fire often occurs at the titanium alloy rotor blade location, the titanium fire containment test device of this invention is designed with the ignition element 400 to simulate the titanium alloy rotor blade of the compressor. Igniting the ignition element 400 simulates the titanium fire generation process of the rotor blade.

[0050] In related technologies, the test method for examining the titanium fire containment of compressor casings typically involves developing a friction ignition test bench based on actual engine components. This test bench mainly reproduces titanium fire by adjusting the radial clearance of the compressor rotor blade tips. During the test, the clearance of the last few stages of the compressor is adjusted to the minimum, and titanium fire is generated through friction between the blade tips and the casing. The casing's titanium fire containment is examined by inspecting and disassembling it during and after the titanium fire occurs. This technical solution matches the actual process of titanium fire in the compressor, but titanium fire can cause damage and burnout to almost all compressor blades, and the test cycle and cost are too high.

[0051] The titanium fire containment test device of the present invention addresses the question of whether titanium fire in compressor titanium alloy rotor blades will burn through the casing. It models the titanium alloy rotor blade as an ignition element 400, and uses a first test housing 100 and a second test housing 200 to simulate the compressor casing and a test blade 300 to simulate the stator blade. The ignition element 400 is ignited to simulate the titanium fire process, thereby verifying whether the fire resistance performance of the compressor casing can meet the requirements for titanium fire prevention. The device has a simple configuration, compact structure, and low test cycle and cost.

[0052] In this invention, the first test housing 100 and the second test housing 200 simulating the compressor casing are made of non-titanium alloy materials; the ignition element 400 simulating the front row titanium alloy rotor blades 1 is made of titanium, and the titanium alloy used should be of the same material as the front row titanium alloy rotor blades 1 of the compressor, that is, the grade of the titanium alloy material of the two should be consistent; the test blade 300 simulating the rear row stator blades can be made of titanium alloy or alloy steel, depending on the stator blades of the actual compressor. If the test blade 300 is made of titanium alloy, a flame-retardant coating can be added to the surface to examine the flame-retardant performance of the coating; if the test blade 300 is made of alloy steel, no flame-retardant coating is required on the surface.

[0053] like Figure 1 , Figure 4 as well as Figure 5 As shown, in one embodiment, the titanium fire containment test apparatus further includes an air inlet structure 500. Figure 1 In the titanium fire containment test apparatus shown, the air intake structure 500 is connected to the first end 110 of the first test housing 100 and the first end 210 of the second test housing 200.

[0054] The air intake structure 500 has an air intake channel 510. The air intake structure 500 is connected to the first test housing 100 and the second test housing 200. The air intake channel 510 is connected to the test chamber 10 so that the test airflow can enter the test chamber 10 from the air intake channel 510.

[0055] Specifically, the first test housing 100 and the second test housing 200 are provided with a plurality of connection holes. Depending on the purpose of connection, the connection holes may include: a first connection hole 11 for connecting with the air intake structure 500 and a second connection hole 12 for connecting the first test housing 100 and the second test housing 200.

[0056] The first connection hole 11 is provided at the first end 110 of the first test housing 100 and the first end 210 of the second test housing 200. The first end 110 of the first test housing 100 and the first end 210 of the second test housing 200 are facing the intake structure 500.

[0057] The second connection hole 12 is located at the third end 130 of the first test housing 100. Figure 1 The bottom end (shown in the vertical direction) and the third end 230 of the second test housing 200 (shown in the vertical direction) Figure 1 The top point is shown in the vertical direction.

[0058] It should be noted that the first connecting hole 11 and the second connecting hole 12 do not represent the number of connecting holes, but are only used to distinguish the two functional types of connecting holes.

[0059] The first end 520 of the air intake structure 500 is provided with a plurality of mounting holes 530. The mounting holes 530 and the first connecting hole 11 are connected by fasteners 14, thereby realizing the connection between the first test housing 100, the second test housing 200 and the air intake structure 500. The fasteners 14 can be selected as follows: Figure 1 The bolt shown.

[0060] like Figure 2 and Figure 3 As shown, a sealing element 13 is provided between the first end 110 of the first test housing 100 and the first end 520 of the air intake structure 500, and between the first end 210 of the second test housing 200 and the first end 520 of the air intake structure 500, to improve sealing performance. The sealing element 13 has multiple through holes corresponding to the first connection holes 11 of the first test housing 100 and the second test housing 200. The sealing element 13 can be selected as follows: Figure 2 and Figure 3 The sealing gasket shown.

[0061] Mounting holes 530 surround the first end 520 of the intake structure 500, which can improve connection stability.

[0062] Optionally, such as Figure 4 As shown, the angle between the central axis YY of the intake channel 510 of the intake structure 500 and the central axis XX of the test chamber 10 is the intake angle α, which ranges from 15° to 65°, to match the airflow angle under the actual working state of the compressor. Since the compressor has a certain intake angle during actual operation, and different intake angles at different working states, the titanium fire containment test device of the present invention matches the intake angle to "the angle between the selected central axis YY and the central axis XX of the test chamber 10" according to a certain working state.

[0063] The titanium fire containment test device of the present invention ensures that the mainstream flow velocity, temperature and pressure of the test airflow when titanium fire occurs conforms to the actual engine operating conditions by designing the air intake structure 500.

[0064] The ignition element 400 in this invention can be selected as a laser ignition method. Specifically, the air intake structure 500 has a laser incident window 540, which is provided with germanium glass. The ignition element 400 in this invention can also be selected as a flame impact ignition, friction ignition, or other ignition methods; this invention is not limited thereto.

[0065] In one embodiment, the air intake structure 500 has an observation window 550, which is equipped with a translucent glass. The combustion status of the first test housing 100, the second test housing 200, and the ignition element 400 and the test blade 300 inside the test chamber 10 can be captured by a camera device outside the observation window 550.

[0066] like Figures 1 to 3 As shown, in one embodiment, the test blade 300 further includes a rotating shaft 320 connected to the blade body 310. The rotating shaft 320 is located at the end of the blade body 310. The titanium fire containment test apparatus of the present invention also includes a rocker arm 600. The fourth end 140 of the first test housing 100 ( Figures 1 to 3 The test blade 300 (shown as the top vertically) has a through hole 102. The shaft 320 of the test blade 300 passes through the through hole 102 of the first test housing 100 and is connected to the rocker arm 600. When the rocker arm 600 rotates, it drives the shaft 320 to rotate along its axial direction, thereby driving the blade body 310 of the test blade 300 to rotate. In this way, by changing the relative positional relationship between the rocker arm 600 and the first test housing 100 or the angle between the rocker arm 600 and the first test housing 100, the spatial position of the blade body 310 of the test blade 300 within the test chamber 10 can be changed.

[0067] Considering the intake angle of the compressor in actual operation, when encountering other operating states of the compressor in actual operation, the intake angle of the test blade 300 can be matched by adjusting the rotation of the rocker arm 600, thereby driving the blade body 310 of the test blade 300 to rotate.

[0068] Furthermore, the titanium fire containment testing apparatus also includes a rotating base 700. The rotating base 700 is used to fix the rocker arm 600 after it rotates, thereby maintaining the circumferential angle of the blade body 310 of the test blade 300. The rotating base 700 is detachably connected to the first test housing 100. One end of the rocker arm 600 is fixedly connected to the rotation shaft 320 of the test blade 300, and the other end of the rocker arm 600 is fixedly connected to the rotating base 700. The rocker arm 600 and the rotating base 700 are detachably fixedly connected by bolts.

[0069] The position of the rotating base 700 relative to the first test housing 100 changes, thereby causing the circumferential angle of the blade 310 of the test blade 300 to change.

[0070] refer to Figure 2 and Figure 3 The rotating base 700 and the first test housing 100 are detachably connected by at least one housing connection hole. The rotating base 700 is provided with at least one first opening 701, through which the fastener 14 can pass to fix its position.

[0071] The rotating base 700 includes a first support plate 710 and a second support plate 720, which have an L-shaped cross-section. After the rotating base 700 is fixed to the first test housing 100 through the first opening 701 on the first support plate 710, the second support plate 720 of the rotating base 700 extends toward the air intake structure 500.

[0072] The inner wall 101 of the first test housing 100 can be made as follows: Figure 6 and Figure 7 The three-dimensional shape of the test blade 300 shown makes the airflow velocity distribution on the surface of the test blade 300 closer to the actual working conditions inside the engine.

[0073] The inner wall 101 of the first test housing 100 can also be made as follows: Figure 8 The geometric shape of the plane shown can reduce processing time and cost.

[0074] The titanium fire containment test apparatus of the present invention includes a fixing portion 410 and an ignition portion 420 connected to the fixing portion 410. The fixing portion 410 of the ignition portion 400 is connected to the first test housing 100. The ignition portion 420 of the ignition portion 400 is located within the air intake channel 510 of the air intake structure 500, and is located upstream of the first test housing 100, the second test housing 200, and the test blade 300 in the flow path of the test airflow. In this embodiment, the ignition portion 420 of the ignition portion 400 simulates... Figure 9 The diagram shows the configuration of the front row of titanium alloy rotor blades 1 in the actual compressor meridional structure. (See diagram for example.) Figure 9 As shown, the front row of titanium alloy rotor blades 1 is located in Figure 9 The front row of titanium alloy rotor blades 1 is located on the left side of the stator blades, in front of the stator blades. The configuration of the front row of titanium alloy rotor blades 1, i.e., the geometric parameters of the front row of titanium alloy rotor blades 1, includes, but is not limited to, the following: Figure 9 The front row titanium alloy rotor blade 1 shown has a blade tip width l, a wedge angle θ (the angle between the casing and the rotor blade), a distance k between the blade tip and the rear row stator blades, and a blade body height h.

[0075] like Figure 10 As shown, the ignition element 400 also includes an extension 430 connected to the fixing portion 410. The extension 430 and the fixing portion 410 are L-shaped, and the extension 430 extends towards... Figure 10 The left side extends out to support the lower ignition part 420.

[0076] Based on the parameter characteristics of the front row titanium alloy rotor blade 1, such as Figures 10 to 13As shown, based on the propagation path of titanium combustion products with the airflow, the height of the ignition section 420 can be selected as 0.25 to 0.5 times the height h of the front row titanium alloy rotor blades 1, i.e., 0.25h to 0.5h. When titanium fire occurs on the front row titanium alloy rotor blades 1 of the compressor, the combustion products at different heights of the blades flow in different directions with the airflow. The combustion products generated in the middle and bottom positions of the blades will not impact the casing with the airflow. Therefore, the height of the ignition section 420 of this invention can simulate the height of the upper half (0.25h to 0.5h) of the front row titanium alloy rotor blades 1.

[0077] like Figure 11 As shown, based on the actual thickness of the compressor blades and the ease of ignition, the thickness w of the ignition section 420 can be selected from 1mm to 3mm.

[0078] Combination Figure 10 and Figure 11 In one embodiment, the ignition portion 420 is inclinedly disposed on the extension section 430. The wedge angle θ between the ignition portion 420 and the extension section 430 is consistent with the width l, wedge angle θ, and distance k of the front row titanium alloy rotor blades 1 of the actual compressor.

[0079] like Figure 12 As shown, in another embodiment, the wedge angle θ between the ignition portion 420 and the extension 430 is simplified to 90°.

[0080] like Figure 13 As shown, in another embodiment, unlike the T-shaped structure of the extension section 430 and the ignition section 420 in the previous two embodiments, the ignition section 420 and the extension section 430 in this embodiment are V-shaped, and the wedge angle θ between the ignition section 420 and the extension section 430 is consistent with the wedge angle θ of the front row titanium alloy rotor blade 1 of the actual compressor.

[0081] The two embodiments described above employ a simpler ignition section 420 structure, which reduces costs.

[0082] In the above-mentioned embodiments of the ignition section 420, at least one parameter needs to be consistent with the front row titanium alloy rotor blade 1 of the real compressor to ensure the accuracy of the simulation test.

[0083] like Figures 11 to 13 The fixing portion 410 of the igniter 400 and at least one connection hole of the first test housing 100 are detachably connected. The fixing portion 410 of the igniter 400 has at least one second opening 411, through which the fastener 14 can pass to fix its position.

[0084] In one embodiment, there are multiple test blades 300, which are spaced apart within the test chamber 10. Figure 14 As shown, the present invention can employ a structure with dual test blades 300 or more test blades 300 to enhance the damage effect of titanium combustion products on downstream test blades 300. In an embodiment using a single test blade 300 within the test chamber 10, some titanium combustion products will impact the inner wall surface of the test chamber 10; while in an embodiment using multiple test blades 300, more titanium combustion products will impact the test blades 300, which is more conducive to observing and evaluating the secondary damage effect of titanium combustion products on downstream test blades.

[0085] like Figure 1 and Figure 2 As shown, the titanium fire testing apparatus also includes a temperature sensor 810 and a pressure sensor 820 disposed in the frame. The temperature sensor 810 is used to detect the temperature of the test gas flow in the test chamber 10, and the pressure sensor 820 is used to detect the pressure of the test gas flow in the test chamber 10. Both the temperature sensor 810 and the pressure sensor 820 are disposed in the first test housing 100.

[0086] Figure 15 An embodiment of the titanium fire containment test method of the present invention is shown. The titanium fire containment test method of the present invention can be applied to the titanium fire containment test apparatus described in any of the above embodiments. The following is in conjunction with... Figures 1 to 15 This paper elaborates on the containment test method for titanium fire testing.

[0087] The titanium fire containment test method of the present invention includes steps S100 to S400:

[0088] In step S100, the test gas flow is introduced into the test chamber 10, and the ignition element 400 is ignited. The test gas flow is a high-temperature, high-pressure, and high-speed gas flow, and is introduced into the test chamber 10 through the air intake channel 510 of the air intake structure 500.

[0089] A laser can be used to ignite the igniter 400 through the laser incident window 540 (i.e., induce a titanium fire). The combustion products of the titanium fire ignited by the igniter 400 will impact the test blade 300, the first test housing 100, and the second test housing 200 with the high-speed airflow.

[0090] In step S200, the combustion state of the first test housing 100, the second test housing 200, and the test blade 300 is captured by a camera device. In this step, an external high-speed camera monitors whether the first test housing 100 and the second test housing 200 can contain the titanium fire, and the temperature sensor 810 and the pressure sensor 820 record the temperature and pressure changes inside the test chamber 10 in real time.

[0091] In step S300, the test airflow is stopped, and the cooled ignition element 400, the first test housing 100, the second test housing 200, and the test blade 300 are disassembled. Timing begins 15-30 seconds after the ignition element 400 is ignited, and the test airflow is shut off.

[0092] In step S400, the ablation status of the ignition element 400, the first test housing 100, the second test housing 200, and the test blade 300 is analyzed.

[0093] While the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the invention. Any variations and modifications can be made by those skilled in the art without departing from the spirit and scope of the invention. Therefore, any modifications, equivalent changes, and alterations made to the above embodiments based on the technical essence of the present invention, without departing from the scope of the invention, fall within the protection scope defined by the claims of the present invention.

Claims

1. A titanium fire containment testing apparatus for testing the titanium fire containment capacity of a compressor casing, characterized in that, The titanium fire testing device includes a first test shell, a second test shell, test blades, and an ignition element; wherein... The first test housing and the second test housing together form a test chamber, and a test airflow passes through the test chamber. The test blade is disposed within the test chamber; The ignition element is located in the flow path of the test airflow; The ignition element can generate high-temperature products after being ignited, and then the high-temperature products impact the first test housing, the second test housing, and the test blade under the action of the test airflow.

2. The titanium fire containment test apparatus as described in claim 1, characterized in that, The titanium fire containment test device also includes an air intake structure; The air intake structure has an air intake channel; The air intake structure is connected to the first test housing and the second test housing, and the air intake channel is connected to the test chamber so that the test airflow can enter the test chamber from the air intake channel.

3. The titanium fire containment test apparatus as described in claim 2, characterized in that, The angle between the central axis of the air intake channel and the central axis of the test chamber is in the range of 15° to 65°.

4. The titanium fire containment test apparatus as described in claim 2, characterized in that, The air intake structure has a laser incident window for laser transmission, the laser being used to ignite the test blade, and the laser incident window is equipped with germanium glass; and / or The air intake structure has an observation window, and the observation window is equipped with a translucent glass.

5. The titanium fire containment test apparatus as described in any one of claims 1 to 4, characterized in that, The titanium fire containment test device also includes a rocker arm; The test blade includes a rotating shaft and a blade body connected to the rotating shaft, and the blade body is located inside the test chamber; The rotating shaft of the test blade passes through the first test housing and is connected to the rocker arm. The rotation of the rocker arm drives the blade body of the test blade to rotate.

6. The titanium fire containment test apparatus as described in claim 5, characterized in that, The titanium fire containment test apparatus also includes a rotating base; The rotating base is detachably connected to the first test housing; One end of the rocker arm is fixedly connected to the rotating shaft of the test blade, and the other end of the rocker arm is fixedly connected to the rotating base; The position of the rotating base relative to the first test housing changes, thereby causing the circumferential angle of the test blade to change.

7. The titanium fire containment test apparatus as described in claim 6, characterized in that, The first test housing is provided with multiple connection holes for connecting to the air intake structure; The rotating base and at least one of the connection holes of the first test housing are detachably connected.

8. The titanium fire containment test apparatus as described in any one of claims 1 to 4, characterized in that, The ignition element includes a fixing part and an ignition part connected to the fixing part; The fixing portion of the ignition element is connected to the first test housing; The ignition portion of the ignition element is located within the air intake channel of the air intake structure, and is located upstream of the first test housing, the second test housing, and the test blade in the flow path of the test airflow.

9. The titanium fire containment test apparatus as described in claim 8, characterized in that, The ignition element also includes an extension section connected to the fixing portion; The ignition portion is inclinedly disposed on the extension section.

10. The titanium fire containment test apparatus as described in claim 8, characterized in that, The first test housing is provided with multiple connection holes for connecting to the air intake structure; The fixing portion of the ignition element and at least one of the connection holes of the first test housing are detachably connected.

11. The titanium fire containment test apparatus as described in claim 8, characterized in that, The number of test blades is multiple, and they are spaced apart within the test chamber.

12. The titanium fire containment test apparatus as described in claim 11, characterized in that, The number of ignition elements is matched with the number of test blades.

13. The titanium fire containment test apparatus as described in any one of claims 1 to 4, characterized in that, The ignition element is ignited by flame impact or plasma arc; and / or The ignition element is made of the same material as the titanium alloy rotor blades of the compressor.

14. The titanium fire containment test apparatus as described in any one of claims 1 to 4, characterized in that, The test blades are made of titanium alloy or alloy steel.

15. The titanium fire containment test apparatus as described in claim 14, characterized in that, The test blade, made of titanium alloy, has a flame-retardant coating applied to its surface.

16. A method for testing the fire-encapsulation properties of titanium, characterized in that, Applied to the titanium fire containment test apparatus as described in any one of claims 1 to 15; The titanium fire test containment test method includes: The test gas is introduced into the test chamber to ignite the ignition element; The combustion state of the first test housing, the second test housing, and the test blade is captured by a camera device. Stop the flow of the test airflow, and disassemble the cooled ignition element, the first test housing, the second test housing, and the test blade. The ablation status of the ignition element, the first test housing, the second test housing, and the test blade was analyzed.

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