Variable-area compression duct for aircraft engine nozzle

Abstract

The application belongs to the technical field of variable cross-section compressed fuel gas flow channel design of aircraft engine nozzle, and particularly relates to a variable cross-section compressed fuel gas flow channel of aircraft engine nozzle, which is designed by left side wall plates, right side wall plates, upper side wall plates and lower side wall plates made of refractory metal matrix composites, and is connected by bolts made of refractory metal matrix composites, and is spliced with each other, has extremely high high-temperature resistance, meets the temperature requirement of the variable cross-section compressed fuel gas flow channel, can maintain mechanical properties under high-temperature conditions, does not need to additionally set up gas film cooling and heat shield structure, can reduce the complexity of the nozzle structure as a whole, has few connection parts, can avoid problems such as thermal stress mismatch and deformation mismatch, and has relatively light mass.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of variable cross-section compression gas flow channel design of aircraft engine nozzle, and particularly relates to a variable cross-section compression gas flow channel of aircraft engine nozzle. BACKGROUND

[0002] The design constraints of aircraft engine nozzle are extremely strict, including that the wall surface temperature of the inner flow channel is extremely high and has reached the material temperature limit, and the high-temperature gas will generate high pressure, vibration and other asymmetric deflection loads, and the super-high temperature force and heat field jointly act, in addition, the nozzle is located at the tail of the aircraft, has a great influence on the center of gravity of the aircraft, and the weight index is harsh.

[0003] The variable cross-section compression gas flow channel 1 of the nozzle is located between the structure compensator 2 and the expansion edge 3, as shown in Figure 1 The pressure of the gas flowing in the variable cross-section compression gas flow channel 1 is large, and the temperature is high, which is the most complex and most severe design condition, the structure compensator 2 located at the front end of the variable cross-section compression gas flow channel 1 is circular in cross-section, and the expansion edge 3 located at the rear end of the variable cross-section compression gas flow channel 1 is rectangular in cross-section, so that the variable cross-section compression gas flow channel 1 is usually manufactured into a round-to-square component by using a high-temperature alloy, and a gas film cooling scheme is used for temperature reduction, and a heat shield needs to be arranged inside to reduce the scouring effect of high-temperature gas on the structure. This kind of technical scheme has the following defects:

[0004] 1) An additional gas film cooling and heat shield structure is arranged, and the cooling gas needs to be dynamically adjusted with the change of the adjusting mechanism, which greatly increases the complexity of the nozzle structure, and any over-temperature failure of any link will cause the structure to be quickly burned and damaged;

[0005] 2) The surface of the heat shield has reached the material temperature limit, and the mechanical properties are basically lost, which is potentially dangerous;

[0006] 3) The gas film cooling and heat shield structure are connected through fasteners, and under high-temperature conditions, a large number of connections have problems such as thermal stress mismatch and deformation discord, and it is difficult to fully consider all aspects in the design.

[0007] The present application is proposed in view of the existence of the above technical defects. SUMMARY

[0008] The purpose of the present application is to provide a variable cross-section compression gas flow channel of aircraft engine nozzle to overcome or alleviate at least one aspect of the known technical defects.

[0009] The technical scheme of the present application is:

[0010] A variable cross-section compression gas flow channel of aircraft engine nozzle, comprising:

[0011] The left side wall plate is made of refractory metal matrix composite, has an outer dimension of no more than 800mm*500mm*1000mm, is an external grid reinforced wall plate, and has two ear pieces arranged on the outer side of the left side wall plate at two positions where the longitudinal and transverse reinforcing strips intersect, and is used for connecting with the support structure.

[0012] The right side wall plate is made of refractory metal matrix composite, has an outer dimension of no more than 800mm*500mm*1000mm, is an external grid reinforced wall plate, and has two ear pieces arranged on the outer side of the right side wall plate at two positions where the longitudinal and transverse reinforcing strips intersect, and is used for connecting with the support structure.

[0013] The upper side wall plate is made of refractory metal matrix composite, has an outer dimension of no more than 800mm*500mm*1200mm, is an external grid reinforced wall plate, and has two ear pieces arranged on the outer side of the upper side wall plate at two positions where the longitudinal and transverse reinforcing strips intersect, and is used for connecting with the support structure.

[0014] The lower side wall plate is made of refractory metal matrix composite, has an outer dimension of no more than 800mm*500mm*1200mm, is an external grid reinforced wall plate, and has two ear pieces arranged on the outer side of the lower side wall plate at two positions where the longitudinal and transverse reinforcing strips intersect, and is used for connecting with the support structure.

[0015] The left side wall plate, the right side wall plate, the upper side wall plate and the lower side wall plate are connected by the connecting edges arranged on the two sides, and are connected by bolts, the bolts are made of refractory metal matrix composite, and the left side wall plate, the right side wall plate, the upper side wall plate and the lower side wall plate are spliced into a circular square component.

[0016] According to at least one embodiment of the present application, the refractory metal matrix composite in the aircraft engine nozzle variable cross-section compressed gas flow channel is prepared by powder metallurgy with ceramic particles and vanadium, niobium, tantalum, chromium, molybdenum, tungsten, rhenium, titanium, zirconium and hafnium.

[0017] According to at least one embodiment of the present application, in the aircraft engine nozzle variable cross-section compressed gas flow channel, the front end of the left side wall plate is connected to the rear end of the structure compensator through a flange edge by a bolt, the rear end is connected to the front end of the expansion edge through a flange edge by a bolt, and the diameter of the bolt hole on the flange edge of the front end and the rear end of the left side wall plate is 2mm larger than the corresponding bolt.

[0018] The front end of the right side wall plate is connected to the rear end of the structure compensator through a flange edge by a bolt, the rear end is connected to the front end of the expansion edge through a flange edge by a bolt, and the diameter of the bolt hole on the flange edge of the front end and the rear end of the right side wall plate is 2mm larger than the corresponding bolt.

[0019] The front end of the upper side wall plate is bolted to the rear end of the structure compensator through a flange, and the rear end is bolted to the front end of the expansion edge through a flange, the diameter of the bolt hole in the flange of the front end and the rear end of the upper side wall plate is 2mm larger than the corresponding bolt;

[0020] The front end of the lower side wall plate is bolted to the rear end of the structure compensator through a flange, and the rear end is bolted to the front end of the expansion edge through a flange, the diameter of the bolt hole in the flange of the front end and the rear end of the lower side wall plate is 2mm larger than the corresponding bolt.

[0021] According to at least one embodiment of the present application, in the aircraft engine nozzle variable cross-section compressed gas flow channel, the thickness of the left side wall plate is 2mm, the size of the external grid rib is 150mm*200mm, the height of the rib is 15mm, and the thickness of the rib is 4mm;

[0022] The thickness of the right side wall plate is 2mm, the size of the external grid rib is 150mm*200mm, the height of the rib is 15mm, and the thickness of the rib is 4mm;

[0023] The thickness of the upper side wall plate is 2mm, the size of the external grid rib is 150mm*200mm, the height of the rib is 15mm, and the thickness of the rib is 4mm;

[0024] The thickness of the lower side wall plate is 2mm, the size of the external grid rib is 150mm*200mm, the height of the rib is 15mm, and the thickness of the rib is 4mm.

[0025] According to at least one embodiment of the present application, in the aircraft engine nozzle variable cross-section compressed gas flow channel, the left side wall plate, the right side wall plate, the upper side wall plate, and the lower side wall plate are sintered with an oxidation-resistant coating on the surface;

[0026] The oxidation-resistant coating is specifically an aluminum oxide or silicon oxide coating.

[0027] According to at least one embodiment of the present application, in the aircraft engine nozzle variable cross-section compressed gas flow channel, the left side wall plate, the right side wall plate, the upper side wall plate, and the lower side wall plate are sintered with an oxidation-resistant coating on the surface;

[0028] The present application has at least the following beneficial technical effects:

[0029] The variable cross-section compressed fuel gas flow channel of the aircraft engine nozzle disclosed in the above embodiment is designed by left side wall plates, right side wall plates, upper side wall plates and lower side wall plates made of refractory metal matrix composites, connected by bolts made of refractory metal matrix composites, and spliced with each other, has very high high-temperature resistance, meets the temperature requirements of the variable cross-section compressed fuel gas flow channel, can maintain mechanical properties under high-temperature conditions, does not need to additionally set up a film cooling and heat shield structure, can reduce the complexity of the nozzle structure as a whole, has fewer connection parts, can avoid problems such as mismatch of thermal stress and mismatch of deformation, and has relatively light mass. BRIEF DESCRIPTION OF DRAWINGS

[0030] Figure 1 is a structural schematic diagram of the prior art aircraft engine nozzle variable cross-section compressed fuel gas flow channel and the structure compensator and the expansion edge;

[0031] Figure 2 is a schematic diagram of the aircraft engine nozzle variable cross-section compressed fuel gas flow channel provided by the embodiment of the application;

[0032] Figure 3 is a schematic diagram of the left side wall plate provided by the embodiment of the application;

[0033] Figure 4 is a schematic diagram of the upper side wall plate provided by the embodiment of the application;

[0034] Figure 5 is a local schematic diagram of the left side wall plate, the right side wall plate, the upper side wall plate and the lower side wall plate connected by the two sides of the connecting edges and connected by bolts provided by the embodiment of the application;

[0035] Among them:

[0036] 1-variable cross-section compressed fuel gas flow channel; 2-structure compensator; 3-expansion edge; 4-left side wall plate; 5-right side wall plate; 6-upper side wall plate; 7-lower side wall plate.

[0037] In order to better illustrate the embodiment, some components in the drawings may be omitted, enlarged or reduced, and do not represent the size of the actual product. In addition, the drawings are only used for illustrative description and cannot be understood as a limitation of the application. DETAILED DESCRIPTION

[0038] In order to make the technical scheme of the application and its advantages clearer, the technical scheme of the application will be further clearly and completely described in detail below in combination with the drawings. It should be understood that the specific embodiments described herein are only part of the embodiments of the application, and are only used to explain the application, but not to limit the application. It should be noted that, in order to facilitate description, only parts related to the application are shown in the drawings, and other related parts can be referred to the usual design.

[0039] In addition, unless otherwise defined, technical terms or scientific terms used in the description of the application shall be the general meaning understood by those of ordinary skill in the art to which the application belongs. The words used to indicate the position in the description of the application are only used to indicate the relative direction or positional relationship, and the relative positional relationship may also change accordingly when the absolute position of the described object changes. The "includes" used in the description of the application indicates that the elements or objects appearing before the word cover the elements or objects listed after the word and their equivalents, without excluding other elements or objects.

[0040] In addition, it should be further pointed out that, unless otherwise explicitly specified and limited, the "installation", "connection" and similar words used in the description of the application should be understood in a broad sense, for example, the connection can be fixed connection or detachable connection; can be mechanical connection or electrical connection; can be directly connected or indirectly connected through intermediate medium, and those skilled in the art can understand the specific meaning of the application according to the specific circumstances.

[0041] The refractory metal matrix composite is prepared by powder metallurgy with various refractory metals such as vanadium, niobium, tantalum, chromium, molybdenum, tungsten, rhenium, titanium, zirconium, hafnium, etc. and ceramic particles, with low density of about 10 g / cm3, still having high mechanical properties at 2000℃, but it is impossible to directly manufacture blanks for diameters exceeding 1000mm, and the outer contour of 1000mmx500mmx1300mm will also cause material waste. Based on this, the application provides a variable cross-section compression gas flow channel for aircraft engine nozzle, as shown in Figure 2 The left side wall plate 4, as shown in

[0042] The left side wall plate 4, as shown in Figure 3 is made of refractory metal matrix composite, with an outer contour size of not more than 800mmx500mmx1000mm, which is an external grid stiffened wall plate, and two ear pieces are arranged on the outside of the left side wall plate 4, which are arranged at the longitudinal and transverse positions of the two rib strips on the outside of the left side wall plate 4, and are used for connecting with the supporting structure. The front end of the left side wall plate 4 is bolted with the rear end of the structure compensator 2 through the flange edge, and the rear end is bolted with the front end of the expansion edge 3 through the flange edge, and the diameter of the bolt hole on the flange edge of the front end and the rear end of the left side wall plate 4 is 2mm larger than that of the corresponding bolt. The thickness of the left side wall plate 4 is 2mm, and the size of the external grid rib strip is 150mmx200mm, and the rib strip height is 15mm and the thickness is 4mm.

[0043] The right side wall plate 5 and the left side wall plate 4 are of a near-symmetrical structure, are made of refractory metal matrix composite, have an outer dimension of no more than 800mmx500mmx1000mm, are external grid reinforced wall plates, and have two lugs arranged on the outer side of the right side wall plate 5 at two positions where the longitudinal and transverse lugs intersect, and are used for connecting with the supporting structure. The front end of the right side wall plate 5 is bolt-connected with the rear end of the structure compensator 2 through a flange, and the rear end is bolt-connected with the front end of the expansion edge 3 through a flange. The diameter of the bolt hole on the flange of the front end and the rear end of the right side wall plate 5 is 2mm larger than the corresponding bolt. The thickness of the right side wall plate 5 is 2mm, the size of the external grid lugs is 150mmx200mm, the lug height is 15mm, and the lug thickness is 4mm.

[0044] The upper side wall plate 6 is made of refractory metal matrix composite, has an outer dimension of no more than 800mmx500mmx1200mm, is an external grid reinforced wall plate, and has two lugs arranged on the outer side of the upper side wall plate 6 at two positions where the longitudinal and transverse lugs intersect, and is used for connecting with the supporting structure. Figure 4 The front end of the upper side wall plate 6 is bolt-connected with the rear end of the structure compensator 2 through a flange, and the rear end is bolt-connected with the front end of the expansion edge 3 through a flange. The diameter of the bolt hole on the flange of the front end and the rear end of the upper side wall plate 6 is 2mm larger than the corresponding bolt. The thickness of the upper side wall plate 6 is 2mm, the size of the external grid lugs is 150mmx200mm, the lug height is 15mm, and the lug thickness is 4mm.

[0045] The lower side wall plate 7 and the upper side wall plate 6 are not necessarily symmetrical structures, are made of refractory metal matrix composite, have an outer dimension of no more than 800mmx500mmx1200mm, are external grid reinforced wall plates, and have two lugs arranged on the outer side of the lower side wall plate 7 at two positions where the longitudinal and transverse lugs intersect, and are used for connecting with the supporting structure. The front end of the lower side wall plate 7 is bolt-connected with the rear end of the structure compensator 2 through a flange, and the rear end is bolt-connected with the front end of the expansion edge 3 through a flange. The diameter of the bolt hole on the flange of the front end and the rear end of the lower side wall plate 7 is 2mm larger than the corresponding bolt. The thickness of the lower side wall plate 7 is 2mm, the size of the external grid lugs is 150mmx200mm, the lug height is 15mm, and the lug thickness is 4mm.

[0046] The left side wall plate 4, the right side wall plate 5, the upper side wall plate 6, and the lower side wall plate 7 are provided with a sintered oxidation-resistant coating on the surface, and are bolt-connected through the connecting edges arranged on the two sides, as shown in Figure 5 The bolt is made of refractory metal matrix composite. The left side wall plate 4, the right side wall plate 5, the upper side wall plate 6, and the lower side wall plate 7 are spliced into a round-to-square component. The round-to-square component is externally wrapped with a temperature-resistant heat insulation felt, and the thickness of the temperature-resistant heat insulation felt is 25mm.

[0047] The aircraft engine nozzle variable cross-section compressed gas flow channel disclosed in the above embodiment is designed by left side wall plate 4, right side wall plate 5, upper side wall plate 6 and lower side wall plate 7 made of refractory metal matrix composite, connected by bolts made of refractory metal matrix composite, spliced together, has very high high-temperature resistance, can maintain mechanical properties under high-temperature conditions, does not need to additionally set up film cooling and heat shield structure, can reduce the complexity of the nozzle structure as a whole, has few connection parts, can avoid problems such as thermal stress mismatch and deformation mismatch, and has relatively light mass.

[0048] In the aircraft engine nozzle variable cross-section compressed gas flow channel disclosed in the above embodiment, left side wall plate 4, right side wall plate 5, upper side wall plate 6 and lower side wall plate 7 are designed to be made of refractory metal matrix composite, and the outer dimensions are not more than 800mmx500mmx1000mm, 800mmx500mmx

[0049] In the aircraft engine nozzle variable cross-section compressed gas flow channel disclosed in the above embodiment, left side wall plate 4, right side wall plate 5, upper side wall plate 6 and lower side wall plate 7 are designed to be external grid stiffened wall plates, which can guarantee rigidity and reduce external support.

[0050] In the aircraft engine nozzle variable cross-section compressed gas flow channel disclosed in the above embodiment, the diameters of the flange edges on the front end of left side wall plate 4, right side wall plate 5, upper side wall plate 6 and lower side wall plate 7, the rear end of compensator 2 and the front end of expansion edge 3 are 2mm larger than the diameters of the corresponding bolts, which can be used for installation allowance adjustment and can compensate thermal expansion deformation.

[0051] In the aircraft engine nozzle variable cross-section compressed gas flow channel disclosed in the above embodiment, two ear pieces are arranged on the outer sides of left side wall plate 4, right side wall plate 5, upper side wall plate 6 and lower side wall plate 7, which are located at the positions where the longitudinal and transverse intersecting strips are arranged, and the longitudinal and transverse intersecting strips are used for support, which can reduce the local stress directly generated on left side wall plate 4, right side wall plate 5, upper side wall plate 6 and lower side wall plate 7, and avoid local damage of left side wall plate 4, right side wall plate 5, upper side wall plate 6 and lower side wall plate 7.

[0052] In the aircraft engine nozzle variable cross-section compressed gas flow channel disclosed in the above embodiment, sintered oxidation-resistant coating is arranged on the surfaces of left side wall plate 4, right side wall plate 5, upper side wall plate 6 and lower side wall plate 7, which can be alumina or silica coating. The coating has good bonding force with the refractory metal matrix composite, and can guarantee that the coating does not fall off under various force and thermal conditions.

[0053] In the aircraft engine nozzle variable cross-section compressed gas flow channel disclosed in the above embodiment, the circular-to-square structure spliced by left side wall plate 4, right side wall plate 5, upper side wall plate 6 and lower side wall plate 7 is wrapped by temperature-resistant heat insulation felt, which can effectively prevent heat from spreading and transferring into the engine cabin.

[0054] The various embodiments in the specification are described in a progressive manner, with each embodiment focusing on the differences from other embodiments. Similar or identical parts between embodiments can be referred to mutually. In the absence of conflict, the embodiments and technical features in the embodiments of this application can be combined to obtain new embodiments.

[0055] The technical solution of this application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of this application is obviously not limited to these specific embodiments. Without departing from the principles of this application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will all fall within the scope of protection of this application.

Claims

1. A variable-area convergent flowpath for an aircraft engine nozzle, comprising: It comprises: a left side wall plate (4) made of refractory metal matrix composite, with an outer dimension of no more than 800mmx500mmx1000mm, as an external grid reinforced wall plate, with two ear pieces on the outside of the left side wall plate (4) at two places where the longitudinal and transverse intersecting ribs are located, for connecting with the support structure; a right side wall plate (5) made of refractory metal matrix composite, with an outer dimension of no more than 800mmx500mmx1000mm, as an external grid reinforced wall plate, with two ear pieces on the outside of the right side wall plate (5) at two places where the longitudinal and transverse intersecting ribs are located, for connecting with the support structure; an upper side wall plate (6) made of refractory metal matrix composite, with an outer dimension of no more than 800mmx500mmx1200mm, as an external grid reinforced wall plate, with two ear pieces on the outside of the upper side wall plate (6) at two places where the longitudinal and transverse intersecting ribs are located, for connecting with the support structure; a lower side wall plate (7) made of refractory metal matrix composite, with an outer dimension of no more than 800mmx500mmx1200mm, as an external grid reinforced wall plate, with two ear pieces on the outside of the lower side wall plate (7) at two places where the longitudinal and transverse intersecting ribs are located, for connecting with the support structure; The left side wall plate (4), the right side wall plate (5), the upper side wall plate (6), and the lower side wall plate (7) are connected by the connecting edges on both sides through bolts, and the bolts are made of refractory metal matrix composite. The left side wall plate (4), the right side wall plate (5), the upper side wall plate (6), and the lower side wall plate (7) are spliced into a circular square component.

2. The aircraft engine nozzle variable-area compression flow path of claim 1, wherein The refractory metal matrix composite is prepared by powder metallurgy with ceramic particles and metals such as vanadium, niobium, tantalum, chromium, molybdenum, tungsten, rhenium, titanium, zirconium, and hafnium.

3. The aircraft engine nozzle variable-area compression flow path of claim 1, wherein The front end of the left side wall plate (4) is connected to the rear end of the structure compensator (2) through a flange edge by bolts, and the rear end is connected to the front end of the expansion edge (3) through a flange edge by bolts. The diameter of the bolt hole on the flange edge of the front end and the rear end of the left side wall plate (4) is 2mm larger than the corresponding bolt. The front end of the right side wall plate (5) is connected to the rear end of the structure compensator (2) through a flange edge by bolts, and the rear end is connected to the front end of the expansion edge (3) through a flange edge by bolts. The diameter of the bolt hole on the flange edge of the front end and the rear end of the right side wall plate (5) is 2mm larger than the corresponding bolt. The front end of the upper side wall plate (6) is connected to the rear end of the structure compensator (2) through a flange edge by bolts, and the rear end is connected to the front end of the expansion edge (3) through a flange edge by bolts. The diameter of the bolt hole on the flange edge of the front end and the rear end of the upper side wall plate (6) is 2mm larger than the corresponding bolt. The front end of the lower side wall plate (7) is connected to the rear end of the structure compensator (2) through a flange edge by bolts, and the rear end is connected to the front end of the expansion edge (3) through a flange edge by bolts. The diameter of the bolt hole on the flange edge of the front end and the rear end of the lower side wall plate (7) is 2mm larger than the corresponding bolt.

4. The aircraft engine nozzle variable-area compression gas passage according to claim 1, characterized in that, the left side wall plate (4) has a thickness of 2 mm, and the outer grid rib has a size of 150 mm*200 mm, a height of 15 mm and a thickness of 4 mm; the right side wall plate (5) has a thickness of 2 mm, and the outer grid rib has a size of 150 mm*200 mm, a height of 15 mm and a thickness of 4 mm; the upper side wall plate (6) has a thickness of 2 mm, and the outer grid rib has a size of 150 mm*200 mm, a height of 15 mm and a thickness of 4 mm; the lower side wall plate (7) has a thickness of 2 mm, and the outer grid rib has a size of 150 mm*200 mm, a height of 15 mm and a thickness of 4 mm.

5. The aircraft engine nozzle variable-area compression gas passage according to claim 1, characterized in that, the left side wall plate (4), the right side wall plate (5), the upper side wall plate (6) and the lower side wall plate (7) are provided with a surface sintered oxidation-resistant coating; the oxidation-resistant coating is specifically an aluminum oxide or silicon oxide coating.

6. The aircraft engine nozzle variable-area compression gas passage according to claim 1, characterized in that, the left side wall plate (4), the right side wall plate (5), the upper side wall plate (6) and the lower side wall plate (7) are spliced into a round-to-square component, and are externally covered with a temperature-resistant heat insulation felt with a thickness of 25 mm.

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