Shunting ring anti-icing structure and engine

Abstract

The invention provides a flow dividing ring anti-icing structure and an engine. The flow dividing ring anti-icing structure comprises a flow dividing ring and a casing, and the casing and the flow dividing ring define a heating cavity and an exhaust seam communicating with the heating cavity; the stator blade is connected with the casing; the air entraining pipe assembly communicates with the heating cavity and is used for introducing high-temperature entraining air into the heating cavity, so that the high-temperature entraining air is blown to the front edge of the blade top of the stator blade through the exhaust seam; and the stator blade is coated with the thermal barrier coating. Through the arrangement of the thermal barrier coating, in the first aspect, the stator blade and the high-temperature bleed air are separated, so that the high-temperature bleed air is prevented from heat exchange with the stator blade while preventing the stator blade from freezing, the stator blade is prevented from being heated unevenly, the local temperature difference is prevented from being too large, and therefore the thermal stress of the stator blade is greatly reduced; on the second aspect, the thermal barrier coating can also serve as a protective layer, and the sand impact resistance of the stator blade is enhanced; according to the two aspects, the service life of the stator blade is greatly prolonged.

Description

Technical Field

[0001] This invention relates to the field of aero-engines, specifically to a flow divider ring anti-icing structure and an engine. Background Technology

[0002] A typical example of an axial-flow turbofan aero-engine is a compressor that consists of a fan-driven booster stage and a high-pressure compressor. The fan-driven booster stage includes an inlet fan, a booster stage, and an intermediate unit. A splitter ring, located before the zero-stage stator blades of the booster stage, diverts the gas to the inner and outer bypass sections. To prevent icing on the splitter ring and stator blades during operation, high-temperature, high-pressure gas is directed to the heating chamber of the splitter ring, impacting the most icing-prone areas of the splitter ring and stator blades to achieve an anti-icing effect.

[0003] However, in related technologies, the high-temperature induced airflow only blows to a local area on the surface of the stator blade, which will lead to uneven heating of the blade surface, resulting in greater thermal stress on the blade and affecting its lifespan. Summary of the Invention

[0004] The present invention was made to solve the above-mentioned technical problems, and its purpose is to provide a flow divider ring anti-icing structure and an engine that can prevent uneven heating of the blade surface.

[0005] Firstly, this application discloses a flow divider ring anti-icing structure, comprising: a flow divider ring and a housing, the housing and the flow divider ring forming a heating chamber and an exhaust slit communicating with the heating chamber; a stator blade connected to the housing; an air duct assembly communicating with the heating chamber, the air duct assembly being used to introduce high-temperature bleed air into the heating chamber so that the high-temperature bleed air is blown to the leading edge of the stator blade tip through the exhaust slit; and a thermal barrier coating applied to the stator blade. The thermal barrier coating, in a first aspect, separates the stator blade from the high-temperature bleed air, preventing the high-temperature bleed air from icing on the stator blade while avoiding heat exchange between the high-temperature bleed air and the stator blade, thereby preventing uneven heating of the stator blade and preventing excessive local temperature differences, thus significantly reducing the thermal stress on the stator blade; in a second aspect, the thermal barrier coating can also serve as a protective layer, enhancing the stator blade's resistance to sand and gravel impact; combining these two aspects, the service life of the stator blade is significantly improved.

[0006] Optionally, the casing has a flange at one end facing the heating chamber, which divides the heating chamber into a front chamber and a rear chamber. An impact hole is provided on the flange. The bleed pipe assembly, the rear chamber, the impact hole, the front chamber, and the exhaust slit are sequentially connected. This allows the high-temperature bleed air to accurately impact the foremost tip of the flow divider ring, improving the flow divider ring's anti-icing efficiency.

[0007] Optionally, the casing is provided with an exhaust port, which connects to the rear cavity and is located between the exhaust slot and the stator blades. In this way, the exhaust slot and the exhaust port can cooperate with each other. Specifically, the high-temperature airflow output from the exhaust slot, in addition to directly blowing onto the stator blades for anti-icing, can also heat up the low-temperature gas blown into the engine via the fan disc. Meanwhile, the high-temperature bleed air output from the exhaust port is more specifically directed towards the stator blades for anti-icing, thereby improving the anti-icing efficiency of the stator blades.

[0008] Optionally, multiple exhaust vents are provided along the circumference of the casing to achieve better cooling for the multiple stator blades arranged in the casing.

[0009] Optionally, the exhaust slit has a chamfered surface on the side facing the stator blade. This chamfered surface is located near the stator blade, allowing the high-temperature induced air to be blown along the chamfered surface to the stator blade. The chamfered surface, firstly, increases the width of the exhaust slit, enabling the high-temperature induced air to cover a wider area of ​​the stator blade; secondly, since the stator blade tip and the junction with the casing are more prone to icing, the chamfered surface can more effectively guide the high-temperature airflow to the stator blade tip area, preventing icing at this junction and thus improving anti-icing efficiency.

[0010] Optionally, the thermal barrier coating is a space-grade thermal insulation and reflective ceramic layer. The space-grade thermal insulation and reflective ceramic layer (Therma-Cover) is composed of tiny ceramic particles suspended in an inert latex. It possesses high reflectivity, high emissivity, low thermal conductivity, and low heat storage coefficient, exhibiting excellent thermal insulation and reflective functions. When applied to this application, it can more effectively isolate heat and reduce the thermal stress on the stator blades.

[0011] Optionally, the stator blade is made of aluminum-based composite material. Aluminum has many advantages in the manufacture of composite materials, such as light weight, low density, good plasticity, and the ease of mastering and processing aluminum-based composite technology. In addition, aluminum-based composite materials have high specific strength and specific stiffness, good high-temperature performance, better fatigue and wear resistance, good damping performance, and a low coefficient of thermal expansion, making them widely used in engine manufacturing.

[0012] Optionally, the bleed air assembly includes a main distribution pipe, a circumferential ring pipe, and multiple bleed air pipes connected in sequence. The bleed air pipes are installed in the casing and communicate with the heating chamber. The main distribution pipe is used to introduce high-temperature bleed air into the heating chamber sequentially through the circumferential ring pipe and the multiple bleed air pipes. This improves the uniformity of high-temperature bleed air distribution in the heating chamber, thereby ensuring a uniform distribution of high-temperature bleed air to the multiple stator blades arranged circumferentially, and improving anti-icing efficiency.

[0013] Secondly, this application discloses an engine including a splitter ring anti-icing structure. The splitter ring anti-icing structure is disposed in the turbocharger stage casing assembly, which is located behind the fan disk. The rotor blades and stator blades are alternately arranged along the engine's axial direction. During operation, the cold air introduced by the fan disk easily causes icing on the splitter ring and stator blades. However, the high-temperature bleed air introduced by the splitter ring anti-icing structure of this application can prevent icing on the splitter ring and stator blades, ensuring normal engine operation. Simultaneously, due to the thermal barrier coating, uneven heat distribution caused by the high-temperature bleed air blowing on localized areas of the stator blades can be prevented, thereby avoiding significant thermal stress on the stator blades and ensuring their service life.

[0014] The beneficial effects of this invention are as follows:

[0015] This application discloses a flow divider ring anti-icing structure, comprising: a flow divider ring and a housing, the housing and the flow divider ring forming a heating chamber and an exhaust slit communicating with the heating chamber; a stator blade connected to the housing; an air duct assembly communicating with the heating chamber, the air duct assembly being used to introduce high-temperature bleed air into the heating chamber so that the high-temperature bleed air is blown to the leading edge of the stator blade tip through the exhaust slit; and a thermal barrier coating applied to the stator blade. The thermal barrier coating, in a first aspect, separates the stator blade from the high-temperature bleed air, preventing the high-temperature bleed air from icing on the stator blade while avoiding heat exchange between the high-temperature bleed air and the stator blade, thereby preventing uneven heating of the stator blade and preventing excessive local temperature differences, thus significantly reducing the thermal stress on the stator blade; in a second aspect, the thermal barrier coating can also serve as a protective layer, enhancing the stator blade's resistance to sand and gravel impact; combining these two aspects, the service life of the stator blade is significantly improved. Attached Figure Description

[0016] The above-described features and advantages of the present invention will be better understood after reading the following detailed description of embodiments of the present disclosure in conjunction with the accompanying drawings. In the drawings, components are not necessarily drawn to scale, and components having similar related characteristics or features may have the same or similar reference numerals.

[0017] Figure 1 It is a structural diagram of the engine;

[0018] Figure 2This is a structural diagram of the booster stage casing assembly of the present invention;

[0019] Figure 3 This is the present invention. Figure 2 Enlarged view of point I;

[0020] Figure 4 This is the present invention. Figure 3 Enlarged view at point II;

[0021] Figure 5 This is the present invention. Figure 3 Sectional view along axis AA;

[0022] Figure 6 This is a structural diagram of the air intake tube assembly of the present invention;

[0023] Figure 7 This is the stress field result without a thermal barrier coating.

[0024] Figure 8 This is the stress field result of the thermal barrier coating set in this invention.

[0025] Explanation of reference numerals in the attached figures:

[0026] 10-Boost stage casing assembly,

[0027] 100-Shunting Ring,

[0028] 200 - Casing, 210 - Flange, 211 - Impact Hole, 220 - Exhaust Hole

[0029] 300 - Heating chamber, 320 - Front chamber, 330 - Rear chamber, 310 - Exhaust slit, 311 - Chamfered surface

[0030] 400-Station blade,

[0031] 500 - Air intake tube assembly, 510 - Main distribution tube, 520 - Circumferential ring tube, 530 - Air intake tube

[0032] 600-thermal barrier coating,

[0033] 20-fan plate,

[0034] 30 - Rotor blades. Detailed Implementation

[0035] The present invention will be further described below with reference to specific embodiments and accompanying drawings. More details are set forth in the following description in order to provide a full understanding of the present invention. However, the present invention can obviously be implemented in many other ways different from those described herein. Those skilled in the art can make similar extensions and derivations based on actual application situations without departing from the spirit of the present invention. Therefore, the scope of protection of the present invention should not be limited by the content of this specific embodiment.

[0036] It should be noted that these and other accompanying drawings are merely examples and are not drawn to scale, and should not be construed as limiting the scope of protection of the present invention.

[0037] In related technologies, to prevent icing of the splitter ring and stator blades, high-temperature, high-pressure gas is introduced into the heating chamber of the splitter ring, impacting the areas of the splitter ring and stator blades most prone to icing to achieve an anti-icing effect. However, the high-temperature induced gas flow only reaches a localized area on the stator blade surface, leading to uneven heating of the blade surface and consequently, significant thermal stress on the blade, affecting its lifespan. Therefore, to solve this problem, the technical solution of this application was developed, which is described below in conjunction with... Figures 1 to 8 To elaborate.

[0038] like Figure 3 , Figure 4 and Figure 6 As shown, this application discloses a diversion ring anti-icing structure, which is applied in... Figure 1 and Figure 2 In the supercharger stage housing assembly 10 shown, the supercharger stage housing assembly 10 is installed in the engine and mounted on the rear side of the fan disc 20.

[0039] The anti-icing structure of the flow divider ring of this application includes a flow divider ring 100, a casing 200, stator blades 400, and an air duct assembly 500. The casing 200 and the flow divider ring 100 together form a heating chamber 300 and an exhaust slit 310. The exhaust slit 310 is an annular gap formed by the interval between the casing 200 and the flow divider ring 100, and communicates with the heating chamber 300.

[0040] Stator blades 400 and rotor blades 30 are alternately arranged in the casing 200 along the axial direction of the engine, and multiple stator blades 400 are arranged along the circumference of the engine. The stator blades 400 are connected to the casing 200.

[0041] Among them, the stator blades 400 located near the fan disk 20 in the supercharger stage casing assembly 10 are zero-stage stator blades. In actual operation, the engine flies with the aircraft to high altitudes, and its operating environment temperature is usually 0℃ to -3℃. During operation, the fan disk 20 introduces cold outside air into the engine, which can easily cause icing on the splitter ring 100 and the stator blades 400, thus affecting the normal operation of the engine. Therefore, it is necessary to introduce high-temperature bleed air from the rear of the engine through the bleed air pipe assembly 500, as detailed below:

[0042] The air intake pipe assembly 500 is connected to the heating chamber 300. The air intake pipe assembly 500 is used to introduce high-temperature air into the heating chamber 300 so that the high-temperature air is blown to the leading edge of the stator blade 400 tip through the exhaust slot 310. The temperature of the high-temperature air is about 300°C, which can prevent icing and other phenomena from occurring on the stator blade 400 and the flow divider ring 100.

[0043] However, the high-temperature induced airflow only reaches a localized area on the surface of the stator blade, resulting in uneven heating of the blade surface. Specifically, the leading edge area of ​​the stator blade 400 is exposed to the high-temperature induced airflow and has a high temperature, typically 300°C. Other areas, such as the root and trailing edge of the stator blade 400, are far from the exhaust slit 310 and are less affected by the high-temperature induced airflow, thus having a lower temperature, typically 0°C to -3°C. This uneven temperature distribution can lead to significant thermal stress on the stator blade 400, affecting its lifespan. Therefore, a thermal barrier coating 600 is applied to the surface of the stator blade 400.

[0044] Specifically, such as Figure 7 and Figure 8 As shown, Figure 7 The stress field results are without a thermal barrier coating. The maximum first principal stress of the stator blade 400 is 630.8 MPa. Figure 8 The stress field result of the thermal barrier coating of the present invention is that the first principal stress of the stator blade 400 is 191.6 MPa. By setting the thermal barrier coating, the stress level of the stator blade 400 after setting the thermal barrier coating is reduced by about 70%.

[0045] It is evident that the thermal barrier coating 600 serves two purposes. First, it isolates the stator blades from the high-temperature induced draft gas, preventing the high-temperature induced draft gas from freezing on the stator blades 400 while avoiding heat exchange between them. This prevents uneven heating of the stator blades 400 and excessive local temperature differences, thereby significantly reducing the thermal stress on the stator blades 400. Second, the thermal barrier coating 600 also acts as a protective layer, enhancing the stator blades 400's resistance to sand and gravel impacts. Combining these two aspects, the service life of the stator blades 400 is significantly improved.

[0046] Optionally, such as Figure 3 and Figure 4As shown, the casing 200 has a flange 210 at one end facing the heating chamber 300, which divides the heating chamber 300 into a front chamber 320 and a rear chamber 330. An impact hole 211 is provided on the flange 210. The bleed pipe assembly 500, the rear chamber 330, the impact hole 211, the front chamber 320, and the exhaust slit 310 are sequentially connected. High-temperature bleed air will sequentially pass through the bleed pipe assembly 500, the rear chamber 330, the impact hole 211, the front chamber 320, and the exhaust slit 310 and be blown to the stator blade 400. This allows the high-temperature bleed air to accurately impact the foremost tip of the flow divider ring 100, improving the anti-icing efficiency of the flow divider ring 100.

[0047] Optionally, the flange 210 is an annular flange arranged around the casing 200, and multiple impact holes 211 can be arranged around the flange 210, so that the high-temperature induced air is evenly distributed in the front cavity 320, and then blown to multiple stator blades 400 arranged around the circumference, thereby improving the anti-icing efficiency of the split ring 100 and the stator blades 400.

[0048] Optionally, such as Figures 3-5 As shown, the casing 200 is provided with an exhaust port 220, which connects to the rear cavity 330 and is located between the exhaust slot 310 and the stator blade 400. Thus, the exhaust slot 310 and the exhaust port 220 can cooperate with each other. Specifically, the high-temperature airflow output from the exhaust slot 310, in addition to directly blowing onto the stator blade 400 for anti-icing, can also heat up the low-temperature gas blown into the engine through the fan disc 20. Meanwhile, the high-temperature bleed air output from the exhaust port 220 is more specifically directed towards the stator blade 400 for anti-icing, thereby improving the anti-icing efficiency of the stator blade 400.

[0049] Optionally, multiple exhaust ports 220 are provided along the circumference of the casing 200 to achieve better cooling effect for the multiple stator blades 400 arranged in the casing 200.

[0050] Optionally, the exhaust slit 310 has a chamfered surface 311 on the side of the slit facing the stator blade 400. The chamfered surface 311 is located on the side of the slit close to the stator blade 400, and the high-temperature exhaust gas can be blown to the stator blade 400 along the chamfered surface 311.

[0051] The chamfered surface 311 has two advantages. First, it increases the width of the exhaust slit 310, allowing the high-temperature induced air to cover a wider area on the stator blade 400. Second, the stator blade tip and the junction of the stator blade 400 and the casing 200 are more prone to icing, and the high-temperature airflow can be more effectively guided to the stator blade tip area via the chamfered surface 311 to prevent icing at the stator blade tip and the junction of the stator blade 400 and the casing 200, thereby improving anti-icing efficiency.

[0052] Optionally, the thermal barrier coating 600 is a space-grade thermal insulation and reflective ceramic layer. The space-grade thermal insulation and reflective ceramic layer (Therma-Cover) is composed of tiny ceramic particles suspended in inert latex. It has high reflectivity, high emissivity, low thermal conductivity, and low heat storage coefficient, and has excellent thermal insulation and reflective functions. When applied to this application, it can more effectively isolate heat and reduce the thermal stress of the stator blade 400.

[0053] Optionally, the stator blade 400 is an aluminum-based composite material. Aluminum has many advantages in the manufacture of composite materials, such as light weight, low density, good plasticity, and the ease of mastering and processing aluminum-based composite technology. In addition, aluminum-based composite materials have high specific strength and specific stiffness, good high-temperature performance, better fatigue and wear resistance, good damping performance, and a low coefficient of thermal expansion, making them widely used in engine manufacturing.

[0054] Optionally, such as Figure 6 As shown, the bleed air assembly 500 includes a main distribution pipe 510, a circumferential ring pipe 520, and multiple bleed air pipes 530 connected in sequence. The bleed air pipes 530 are installed in the casing 200 and connected to the heating chamber 300. The main distribution pipe 510 is used to introduce high-temperature bleed air into the heating chamber 300 sequentially through the circumferential ring pipe 520 and the multiple bleed air pipes 530. In this way, the uniformity of the distribution of high-temperature bleed air in the heating chamber 300 can be improved, thereby making the high-temperature bleed air volume obtained by the multiple stator blades 400 arranged circumferentially uniform and improving the anti-icing efficiency.

[0055] like Figure 1 and Figure 2As shown, this application also discloses an engine including the aforementioned anti-icing structure for the splitter ring. The anti-icing structure is disposed on the turbocharger stage casing assembly 10, which is located behind the fan disk 20. The rotor blades 30 and stator blades 400 are alternately arranged along the engine's axial direction. During operation, the cold air introduced by the fan disk 20 easily causes icing of the splitter ring 100 and stator blades 400. The high-temperature bleed air introduced by the anti-icing structure of this application can prevent icing of the splitter ring 100 and stator blades 400, ensuring normal engine operation. Simultaneously, the thermal barrier coating 600 prevents uneven heat distribution caused by the high-temperature bleed air blowing on localized areas of the stator blades 400, thereby avoiding significant thermal stress on the stator blades 400 and ensuring their service life.

[0056] 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 diversion ring anti-icing structure, characterized in that, include: A flow divider ring (100) and a housing (200), the housing (200) and the flow divider ring (100) forming a heating chamber (300) and an exhaust slit (310) communicating with the heating chamber (300); Stator blade (400) is connected to the casing (200); An air intake tube assembly (500) is connected to the heating chamber (300). The air intake tube assembly (500) is used to introduce high-temperature air into the heating chamber (300) so that the high-temperature air is blown through the exhaust slot (310) to the leading edge of the stator blade (400). A thermal barrier coating (600) is applied to the stator blade (400).

2. The anti-icing structure of the diversion ring according to claim 1, characterized in that, The casing (200) has a flange (210) at one end facing the heating chamber (300), the flange (210) divides the heating chamber (300) into a front chamber (320) and a rear chamber (330), and an impact hole (211) is provided on the flange (210); The air intake tube assembly (500), the rear chamber (330), the impact hole (211), the front chamber (320), and the exhaust slit (310) are connected in sequence.

3. The anti-icing structure of the diversion ring according to claim 2, characterized in that, The casing (200) is provided with an exhaust port (220), which communicates with the rear cavity (330) and is located between the exhaust slit (310) and the stator blade (400).

4. The anti-icing structure of the diversion ring according to claim 3, characterized in that, Multiple exhaust ports (220) are provided along the circumference of the casing (200).

5. The anti-icing structure of the diversion ring according to claim 1, characterized in that, The venting slit (310) has a chamfered surface (311) on the side of the slit facing the stator blade (400), and the chamfered surface (311) is located on the side of the slit closest to the stator blade (400). The high-temperature induced air can be blown along the chamfered surface (311) to the stator blade (400).

6. The anti-icing structure of the diversion ring according to any one of claims 1 to 5, characterized in that, The thermal barrier coating (600) is a space-grade thermal insulation and reflective ceramic layer.

7. The anti-icing structure for the diversion ring according to any one of claims 1 to 5, characterized in that, The stator blade (400) is an aluminum-based composite material.

8. The anti-icing structure of the diversion ring according to any one of claims 1 to 5, characterized in that, The air intake pipe assembly (500) includes a main distribution pipe (510), a circumferential ring pipe (520), and a plurality of air intake pipes (530) connected in sequence. The air intake pipes (530) are mounted on the casing (200) and connected to the heating chamber (300). The main distribution pipe (510) is used to introduce high-temperature induced gas into the heating chamber (300) sequentially through the circumferential ring pipe (520) and the plurality of induced gas pipes (530).

9. An engine, characterized in that, The diversion ring anti-icing structure includes any one of claims 1 to 8.

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