Combustion chamber test device with sealing ring and rectifying blade and test method
By designing a combustion chamber test device and adopting a specific structure and connection method, the problem of simulating high-temperature operating conditions of the turbine-guide was solved, achieving high-temperature testing and safety improvement, and ensuring the reliability and safety of the engine.
Patent Information
- Application Number
- CN202411390122.6
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2024-09-30
- Publication Date
- 2026-03-31
AI Technical Summary
Existing test equipment cannot simulate the real high-temperature operating conditions of turbine-guided engines, resulting in inaccurate assessments of cooling performance and lifespan, which limits the engine development progress and safety, and poses a risk of engine failure.
Design a combustion chamber test device, including an intake rectification section, a combustion chamber and turbine guide test section, an outlet rectification and exhaust section, and adopt an outer ring semi-floating hook, an inner ring floating connection, a blade edge combined pin groove, a load-bearing frame + thin-walled edge plate inner and outer edge plate design, and a multi-flexible sealing structure to simulate the high temperature test of the turbine guide.
This method enables high-temperature testing of the turbine's first guide, simulating the actual temperature distribution under engine operating conditions. This improves the accuracy and safety of the test, and avoids engine failures and economic losses caused by insufficient verification.
Smart Images
Figure CN121762224A_ABST
Abstract
Description
Technical Field
[0001] This application relates to combustion chamber test apparatus and test methods. Background Technology
[0002] With advancements in engine technology, the inlet temperature of the turbine first-stage guide vane in modern engines has reached nearly 2000K under high-temperature conditions, and will approach or exceed 2100K under extremely high-temperature conditions. Under these conditions, the turbine first-stage guide vane must withstand thermal loads approaching the limits of its operating temperature, utilizing high-temperature alloy materials, structural design, and cooling technology. Under such conditions, the turbine first-stage guide vane is highly susceptible to blade erosion, breakage, and other malfunctions, jeopardizing the operational safety of the entire engine or core engine. Therefore, during component design, it is essential to verify the turbine first-stage guide vane wall temperature data under high-temperature conditions and conduct evaluation and verification of the turbine first-stage guide vane component design at temperatures above 2000K to further reduce the safety risks during engine / core engine testing.
[0003] The existing testing equipment lacks a scheme to integrate the turbine guide with the annular combustion chamber. This results in the temperature distribution of the high-temperature gas field at the turbine guide inlet failing to simulate the actual operating temperature during turbine guide component testing. Furthermore, the significant difference between the maximum combustion gas temperature and the engine's extreme operating temperature means that the cooling performance and lifespan of the turbine guide at high temperatures can only be obtained through external calculations, with accuracy requiring improvement. Consequently, many extreme operating conditions can only be verified within the core engine, which to some extent restricts the engine's development progress and operational safety during development. Insufficient verification of the turbine guide may lead to core engine failure during engine testing or operation, resulting in engine scrapping and substantial economic losses.
[0004] Therefore, there is a need in the field for a combustion chamber testing device and testing method to fully test the turbine guide at high temperatures, so as to simulate its temperature distribution during operation as much as possible, to achieve the requirement of fully verified turbine guide, improve the safety and reliability of core engine testing and engine operation, and avoid the risk of engine scrapping. Summary of the Invention
[0005] The purpose of this application is to provide a combustion chamber testing apparatus.
[0006] Another objective of this application is to provide a testing method.
[0007] A combustion chamber test apparatus according to a first aspect of this application includes: an intake rectification section; a combustion chamber and turbine guide test section, including a nozzle assembly, a flame tube assembly, and a turbine guide assembly; an outlet rectification and exhaust section, including rectification blades, an exhaust section outer casing, and an exhaust section inner casing, wherein the rectification blades are respectively connected to the exhaust section outer casing and the exhaust section inner casing at their radial ends; wherein the rectification blades are integrally connected to the exhaust section outer casing via rectification blade pressure plates and rectification blade outlet mounting plates, and the rectification blade pressure plates and rectification blade outlet mounting plates are respectively connected and fixed to the exhaust section outer casing via a first mounting component and a second mounting component; the rectification blade outlet mounting plates have circumferentially evenly distributed rectification blade pins; the rear ends of the rectification blades are hooked onto the rectification blade pins by forming pin grooves in pairs, and the front ends are pressed by the rectification blade pressure plates through a sealing ring, the sealing ring being compressible; and a cooling system fluidly connected to the outlet rectification and exhaust section to cool the outlet rectification and exhaust section.
[0008] In one or more embodiments of the aforementioned test apparatus, the rectifier blade has a pin groove ring and a pin groove wall on each of the two sides of the mounting edge on the rear side of the outer edge plate. The pin groove ring and the pin groove wall together form a rectangular pin groove, which engages with the rectifier blade pin.
[0009] In one or more embodiments of the test apparatus, the fit is a clearance fit or a transition fit.
[0010] In one or more embodiments of the test apparatus, the pin groove ring is located at the edge of the blade's mounting edge on the rear side of the outer edge plate and has an open structure.
[0011] In one or more embodiments of the test apparatus, the pin groove ring further includes a vertical end-wall pin groove positioning baffle for axial positioning of the pin groove, wherein the pin groove positioning baffle and the pin groove ring have an open structure.
[0012] In one or more embodiments of the test apparatus, the rectifier blade includes a blade body, an outer edge plate, and an inner edge plate, wherein the outer edge plate and the inner edge plate have blade body contour ribs, which are connected to the blade circumferential sealing ribs through a plurality of edge plate reinforcing ribs around them, and the interior of the blade body is reinforced by a cavity wall that runs through the blade body.
[0013] In one or more embodiments of the test apparatus, the remaining portions of the outer and inner edge plates are thin-walled structures serving as skin, with the flow channel side used to form a gas flow channel, and the wall thickness is 1.5–2.5 mm; the blade profile ribs have a thickness of 4.5–7.5 mm, the blade cavity wall thickness is 2.5–4.5 mm, and the edge plate reinforcing ribs have a width of 3–5 mm and an angle between them and the blade profile ribs is in the range of 70–110°.
[0014] In one or more embodiments of the aforementioned test apparatus, the rectifier blade has multiple flexible seals: on the outside of the rectifier blade, the front end is sealed by an outer ring sealing ring, and the rear end adopts an overlap that allows for small gap leakage; on the inside of the rectifier blade, the front end is sealed by an inner ring sealing ring, and the rear end is sealed by a sealing plate.
[0015] According to a test method of the second aspect of this application, the test is conducted using the test apparatus described in the first aspect.
[0016] In one or more embodiments of the test method, the model of the combustion chamber and turbine of the core engine to be tested is determined, and the nozzle assembly, flame tube assembly and turbine guide assembly of the test apparatus are configured to be the same as the nozzle assembly, flame tube assembly and turbine guide assembly of the combustion chamber of the core engine to be tested.
[0017] In one or more embodiments of the test method, after determining that the turbine of the core machine under test can operate normally under extreme conditions by conducting tests using the test apparatus as described in the first aspect, the extreme condition test of the core machine is then carried out.
[0018] The beneficial effects of the embodiments described above include, but are not limited to, the use of a connection structure of "outer ring semi-floating hook and inner ring floating connection", a positioning structure of "blade edge combined pin groove", an inner and outer edge plate design structure of "load-bearing frame + thin-walled edge plate" and a multi-layer flexible sealing structure, enabling the OGV rectifier blade to withstand extremely high thermal loads caused by high temperatures approaching Ma>0.8, total incoming flow temperature greater than 2000K, and thermal erosion from high-speed swirling flow. Through the use of this OGV rectifier blade, the entire testing device can simulate the temperature distribution and temperature level under real engine operating conditions, and raise the turbine guide temperature to above 2000K, thereby fully testing the turbine guide at high temperatures and fulfilling the requirement for fully verified turbine guide. This can prevent failures during core engine testing or engine operation due to insufficient turbine guide verification, which could lead to engine scrapping and huge economic losses. Attached Figure Description
[0019] The above and other features, properties, and advantages of this application will become more apparent from the following description taken in conjunction with the accompanying drawings and embodiments, in which the same reference numerals always denote the same features. It should be noted that these drawings are merely illustrative and are not drawn to scale, and should not be construed as limiting the scope of protection actually claimed by this application, wherein:
[0020] Figure 1 This is a schematic diagram of the structure of a combustion chamber test apparatus according to one embodiment;
[0021] Figure 2This is a partial structural schematic diagram of a combustion chamber test apparatus according to one embodiment;
[0022] Figure 3 This is a schematic diagram of the rectifier blade layout of a combustion chamber test apparatus according to one embodiment.
[0023] Figure 4 This is a schematic diagram of the rectifier blade outlet mounting plate of a combustion chamber test device according to one embodiment.
[0024] Figure 5 This is a schematic diagram of the combined pin groove on the edge of the rectifier blade of a combustion chamber test device according to an embodiment.
[0025] Figure 6 This is a schematic diagram of the combination pin groove and pin connection at the edge of the rectifier blade of a combustion chamber test device according to an embodiment.
[0026] Figure 7 This is a schematic diagram of the rectifier blade edge plate of a combustion chamber test device according to an embodiment.
[0027] Figure 8 This is a schematic diagram of the rectifier blade layout structure of a combustion chamber test device according to one embodiment.
[0028] Figure 9 This is a schematic flowchart of an embodiment of the test method. Detailed Implementation
[0029] Reference will now be made in detail to various embodiments of this application, examples of which are shown in the accompanying drawings and described below. Although this application will be described in conjunction with exemplary embodiments, it should be understood that this specification is not intended to limit this application to those exemplary embodiments. Rather, this application is intended to cover not only these exemplary embodiments, but also various alternatives, modifications, equivalents, and other embodiments that may be included within the spirit and scope of this application as defined by the appended claims.
[0030] In the following description, the orientation or positional relationship indicated by the terms "upstream", "downstream" or other directional terms is based on the orientation or positional relationship shown in the accompanying drawings and is only for the convenience of describing this application and simplifying the description, and is not intended to indicate or imply that the device or component referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this application.
[0031] Furthermore, this application uses specific terms to describe its embodiments. For example, "an embodiment" and / or "one embodiment" refers to a particular feature, structure, or characteristic associated with at least one embodiment of this application. Therefore, it should be emphasized and noted that "an embodiment" or "one embodiment" mentioned twice or more in different locations in this specification do not necessarily refer to the same embodiment. In addition, certain features, structures, or characteristics in one or more embodiments of this application can be appropriately combined.
[0032] refer to Figures 1 to 8 As shown, the combustion chamber test apparatus may include an intake rectification section 1, a combustion chamber and turbine guide test section 2, an outlet rectification and exhaust section 3, and a cooling system.
[0033] like Figure 1 as well as Figure 2 As shown, the meaning of intake rectifier section 1 is self-explanatory; it is used to rectify the intake air between the combustion chamber and the turbine guide section 2. Intake rectifier section 1 may include multiple circumferentially distributed support plates 15, which are connected to the outer casing 19 and the inner casing 16 of the intake rectifier section at their radial ends, but are not limited thereto.
[0034] The combustion chamber and turbine guide test section 2 includes a nozzle assembly 6, a flame tube assembly 7, and a turbine guide assembly 8. The nozzle assembly 6, flame tube assembly 7, and turbine guide assembly 8 are replaceable parts, identical to the nozzle assembly, flame tube assembly, and turbine guide assembly of the combustion chamber of the core engine under test, and the relative deformation of the three components is completely consistent with the parts. This ensures that the test data accurately reflects the working state of the components in the engine.
[0035] The combustion chamber described in the embodiments uses a full-annular combustion chamber as an example, but is not limited thereto. The meaning of turbine first guide vane is similar to that in the art, that is, the first stage guide vane of the turbine, usually the first stage guide vane of a high-pressure turbine.
[0036] The outlet rectifier and exhaust section 3 includes rectifier blades 9, an outer exhaust section casing 10, and an inner exhaust section casing 11. The rectifier blades 9 are connected to the outer exhaust section casing 10 and the inner exhaust section casing 11 at their radial ends, respectively. The specific structure of the rectifier blades 9 can be an OGV (outlet guide vane) blade, but is not limited thereto.
[0037] The OGV rectifier blade 9 is integrated with the exhaust section outer casing 10 via the rectifier blade clamping plate 14 and the rectifier blade outlet mounting plate 23. The rectifier blade clamping plate 14 and the rectifier blade outlet mounting plate 23 are connected and fixed to the exhaust section outer casing 10 via a first mounting component 27 (e.g., a front mounting bolt) and a second mounting component 28 (e.g., a rear mounting bolt). The rectifier blade outlet mounting plate 23 has circumferentially evenly distributed rectifier blade pins 29 and an unloading groove 30 on its outer side. The rear end of the OGV rectifier blade 9 is attached to the rectifier blade pin 29 by forming a pin groove 31 through a combination of two. The front end is pressed by the rectifier blade pressure plate 14 through the outer ring W sealing ring 22. With the help of the low rigidity and compressibility of the outer ring W sealing ring 22, the OGV rectifier blade 9 is formed into an approximately attached semi-floating structure with "elastic floating front end" and "attached rear end". This solves the thermal mismatch problem between the high temperature OGV rectifier blade 9 and the relatively low temperature exhaust section casing 10, and at the same time can effectively transfer the aerodynamic force to the rear.
[0038] In some embodiments, the OGV rectifier blade 9 has a pin groove ring 31 and a pin groove wall 32 on each side edge of the mounting edge 33 on the rear side of the outer edge plate. The pin groove ring 31 and the pin groove wall 32 together form a rectangular pin groove, which engages with the rectifier blade pin 29. This engagement can be a clearance fit or a transition fit depending on the precision required. The pin groove ring 31 is located at the edge of the mounting edge 33 on the rear side of the outer edge plate and is open. This breaks the edge stiffness boundary, thereby eliminating the thermal stress of the pin groove itself. The pin groove ring 31 also has a vertical end wall pin groove positioning baffle 34 for axial positioning of the pin groove. This baffle is also open to the pin groove ring 31.
[0039] In some embodiments, the OGV rectifier blade 9 includes a blade body 40, an outer edge plate 41, and an inner edge plate 42. The outer edge plate 40 and the inner edge plate 41 adopt a "load-bearing frame + thin-walled edge plate" design concept. That is, the outer edge plate 40 and the inner edge plate 41 have blade body contour ribs 38, which are connected to the blade circumferential sealing ribs 39 through multiple edge plate reinforcing ribs 36 around them. The blade body is reinforced by a cavity wall 37 that runs through the blade body. The remaining parts of the edge plate are thin-walled structures, serving as skin, and their flow channel side is used to form a gas flow channel with a wall thickness of 1.5 to 2.5 mm. The blade body contour ribs 38 have a thickness of 4.5 to 7.5 mm, the blade body cavity wall 37 has a thickness of 2.5 to 4.5 mm, and the edge plate reinforcing ribs 36 have a width of 3 to 5 mm and an angle between them and the blade body contour ribs 38 in the range of 70 to 110°.
[0040] In some embodiments, the OGV rectifier blade 9 employs a multi-layer flexible sealing structure. Specifically, the outer front end of the OGV rectifier blade 9 is sealed by an outer ring W sealing ring 22, while the rear end uses an overlap that allows for small-gap leakage. On the inner side of the OGV rectifier blade 9, the front end is sealed by an inner ring W sealing ring 21, and the rear end is sealed by a sealing plate 20. Utilizing the deformation-insensitive sealing performance of the sealing plate type structure, the OGV rectifier blade 9 achieves good sealing while maintaining a floating connection. This ensures that most of the cooling air is used for cooling the OGV rectifier blade 9, significantly reducing the amount of cooling air used and lowering the cooling air requirements of the test system.
[0041] In some embodiments, the intake rectifier section 1, the combustion chamber and turbine guide section 2, and the outlet rectifier and exhaust section 3 are distributed sequentially from upstream to downstream. The intake rectifier section 1, the combustion chamber and turbine guide section 2, and the outlet rectifier and exhaust section 3 are connected by flanges, forming an in-line structure. This structure is simple, reliable, and easy to assemble.
[0042] The nozzle assembly 6, flame tube assembly 7, and turbine guide assembly 8 in the full-ring combustion chamber and turbine guide test section 2 can be completely identical to the engine component design, and the relative deformation of the three components is completely consistent with the component. This ensures that the test data can accurately reflect the working state of the components in the engine. The cooling gas system 4 provides heated and pressurized cooling gas to the OGV rectifier blades 9. The heated cooling gas forms a film cooling on the OGV surface, and at the same time, the heated cooling gas can effectively alleviate the high stress problem caused by the overcooling of the internal solid structure of the OGV. Figure 2 As shown.
[0043] In some embodiments, the cooling system may include a cooling gas system 4, the outlet of which supplies cooling gas to the rectifier blade 9 to form a film cooling on the rectifier blade 9. For example, the cooling gas system 4 may supply heated and pressurized cooling gas to the rectifier blade 9, forming a film cooling on the blade surface by heating the cooling gas. At the same time, the heated cooling gas can effectively alleviate the high stress problem caused by the overcooling of the internal solid structure of the blade.
[0044] Continue to refer to Figures 1 to 2 As shown, in some embodiments, the cooling gas system 4 may further include a first cooling gas path 12 and a second cooling gas path 13, which respectively supply cooling gas to the upstream and downstream ends of the rectifier blade 9. (Continue to refer to...) Figures 1 to 2As shown, the cooling system may also include a cooling water system 5, which is connected to the outlet rectifier and exhaust section 3 via a pipe to provide cooling for the outlet rectifier and exhaust section 3. This can further improve the cooling effect, enhance the reliability of the test device, and prevent overheating.
[0045] As mentioned above, for reference Figure 9 As shown, in some embodiments, this application also provides a testing method, which uses the testing apparatus described in the above embodiments to conduct the test.
[0046] Specifically, the test method may include: determining the model of the combustion chamber and turbine of the core engine to be tested, and configuring the nozzle assembly 6, flame tube assembly 7 and turbine guide assembly 8 of the test device to be the same as the nozzle assembly, flame tube assembly and turbine guide assembly of the combustion chamber of the core engine to be tested.
[0047] In some embodiments, the test is conducted using the test apparatus described in the above embodiments. After determining that the turbine of the core machine under test can operate normally under extreme conditions, the extreme condition test of the core machine is then carried out.
[0048] In summary, the beneficial effects of the combustion chamber test apparatus and methods described above include, but are not limited to, the following: By employing a connection structure of "semi-floating outer ring and floating inner ring," a positioning structure of "blade edge combined pin grooves," an inner and outer edge plate design structure of "load-bearing frame + thin-walled edge plate," and a multi-layered flexible sealing structure, the OGV rectifier blades can withstand extremely high thermal loads caused by high temperatures approaching Ma > 0.8, a total incoming flow temperature greater than 2000K, and the thermal erosion of high-speed swirling flow. The use of these OGV rectifier blades allows the entire testing apparatus to simulate the temperature distribution and levels under real engine operating conditions, raising the turbine guide temperature to above 2000K. This ensures thorough high-temperature testing of the turbine guide, fulfilling the requirement for fully verified turbine guide performance. It prevents malfunctions during core engine testing or engine operation due to insufficient turbine guide verification, which could lead to engine failure and significant economic losses.
[0049] While this application discloses preferred embodiments as described above, it is not intended to limit the scope of this application. Any changes and modifications can be made by those skilled in the art without departing from the spirit and scope of this application. Therefore, any modifications, equivalent changes, and alterations made to the above embodiments based on the technical essence of this application without departing from the content of the technical solution of this application shall fall within the protection scope defined by the claims of this application.
Claims
1. A combustion chamber test apparatus characterized by comprising: The test device comprises: an inlet flow straightener section (1); a combustion chamber and turbine guide vane section (2) comprising a nozzle assembly (6), a flame tube assembly (7) and a turbine guide vane assembly (8); an outlet flow straightener and exhaust section (3) comprising straightener vanes (9), an outer exhaust section casing (10) and an inner exhaust section casing (11), the straightener vanes (9) being connected at both radial ends to the outer exhaust section casing (10) and the inner exhaust section casing (11) respectively; wherein the straightener vanes (9) are connected integrally to the outer exhaust section casing (10) via a straightener vane pressure plate (14) and a straightener vane outlet hanging plate (23), the straightener vane pressure plate (14) and the straightener vane outlet hanging plate (23) being connected and fixed to the outer exhaust section casing (10) via a first mounting member (27) and a second mounting member (28) respectively; the straightener vane outlet hanging plate (23) having straightener vane pins (29) distributed uniformly in the circumferential direction, the rear ends of the straightener vanes (9) being hung on the straightener vane pins (29) via pin grooves (31) formed by two-by-two combination, and the front ends being pressed by the straightener vane pressure plate (14) via a seal ring (22), the seal ring (22) being compressible; and a cooling system fluidly connected to the outlet flow straightener and exhaust section (3) to cool the outlet flow straightener and exhaust section (3).
2. The test device of claim 1, wherein The straightener vanes (9) have a pin groove ring (31) and a pin groove wall (32) on both sides of the rear side mounting edge (33) of the outer rim plate respectively; the pin groove ring (31) and the pin groove wall (32) together form a rectangular pin groove and cooperate with the straightener vane pins (29).
3. The test device of claim 2, wherein The cooperation is clearance fit or transition fit.
4. The test device according to claim 2, wherein the pin groove ring (31) is located at the edge of the rear side mounting edge (33) of the outer rim plate of the straightener vane (9) and has an open structure.
5. The test device of claim 2, wherein The pin groove ring (31) further comprises a vertical end wall pin groove positioning baffle (34) for axial positioning of the pin groove, and the pin groove positioning baffle (34) and the pin groove ring (31) have an open structure.
6. The test device of claim 1, wherein The straightener vane (9) comprises a vane body (40), an outer rim plate (40) and an inner rim plate (41), wherein the outer rim plate (40) and the inner rim plate (41) have a vane body profile rib (38), are connected to a vane circumferential seal rib (39) via a plurality of rim plate reinforcing ribs (36) around them, and the inside of the vane body is reinforced by a cavity wall (37) penetrating along the vane body.
7. The test device of claim 6, wherein The remaining positions of the outer rim plate (40) and the inner rim plate (41) are thin-walled structures, which are used as a skin to form a gas flow passage on the flow passage side, and the wall thickness is 1.5-2.5 mm; the thickness of the vane body profile rib (38) is 4.5-7.5 mm, the thickness of the vane body cavity wall (37) is 2.5-4.5 mm, and the width of the rim plate reinforcing rib (36) is 3-5 mm and the included angle with the vane body profile rib (38) is in the range of 70-110°.
8. The test device of claim 1, wherein The rectification vane (9) has multiple flexible seals, outside the rectification vane (9), the front end is sealed by an outer ring seal ring (22), and the rear end is sealed by overlapping with a small gap leakage allowed; inside the rectification vane (9), the front end is sealed by an inner ring seal ring (21), and the rear end is sealed by a seal sheet (20).
9. A test method characterized by, The test is performed by using the test device according to any one of claims 1-8.
10. The test method of claim 9, wherein, The model of the combustion chamber and the turbine of the core engine to be tested is determined, and the nozzle assembly (6), the flame tube assembly (7) and the turbine guide assembly (8) of the test device are configured to be the same as the nozzle assembly, the flame tube assembly and the turbine guide assembly of the combustion chamber of the core engine to be tested.
11. The test method of claim 9, wherein, The test is performed by using the test device according to any one of claims 1-8, and the turbine guide of the core engine to be tested is determined to be able to normally operate under the extreme working condition, and then the extreme working condition test of the core engine is performed.