High-temperature and high-pressure floating air-entraining sealing structure

Abstract

The invention discloses a high-temperature and high-pressure floating air-entraining sealing structure, and belongs to the technical field of aero-engine air systems. The structure comprises a combustion chamber casing, an outer culvert casing, an adapter pipe and a bent pipe with a seat, the combustion chamber casing is provided with an air-tight seal floating mechanism, the outer culvert casing is provided with an air exhaust mounting seat, one end of the adapter pipe is in clearance fit with the air-tight seal floating mechanism and is communicated with the interior of a combustion chamber through the air-tight seal floating mechanism, and the other end of the adapter pipe is provided with an air exhaust mounting seat. The other end of the adapter pipe and one end of the bent pipe with the base are jointly installed and fixed to the air exhaust installation base through a plurality of connecting assemblies, and the end, away from the combustion chamber case, of the adapter pipe communicates with the outside through the bent pipe with the base. Sealing is achieved through the internal and external air pressure difference of the combustion chamber cavity and matching of all parts, the sealing performance is good, the service life is prolonged, meanwhile, the structure of the adapter pipe is simplified, and the manufacturing cost of the adapter pipe is reduced. And the adapter pipe is not fixedly connected with the combustion chamber casing, so that the influence of vibration stress on the adapter pipe is reduced.

Description

Technical Field

[0001] The invention relates to a high-temperature and high-pressure floating bleed air sealing structure, belonging to the technical field of aeroengine air systems. Background Art

[0002] The bleed air duct is an important component of the aircraft engine air system. It connects the combustion chamber and the outer casing, safely leads the high-temperature and high-pressure hot air flow in the combustion chamber to the outside of the engine, and then connects with other ducts to transport the hot air. Ultimately, it plays two roles in supporting the pre-chamber pressurization on the engine and preventing icing at the engine inlet.

[0003] At present, the internal high-temperature and high-pressure airflow of aircraft engines is usually directly led out through an integrated duct and sealed with a rubber ring or an expansion ring; the inner casing of existing aircraft engine casings is mostly made of high-temperature alloy materials with higher strength, and the outer casing is made of aluminum alloy materials with lighter texture. The linear expansion coefficients of the two materials are quite different, and the temperature difference between the inner and outer casings is also large, resulting in a large relative displacement of the mounting holes on the inner and outer casings under hot conditions; the integrated duct has a small amount of movement, and the pipeline is easily squeezed and rubbed against the casing wall, which will cause stress inside the pipeline, greatly reducing the service life of the pipeline, and in severe cases will threaten the safety of the engine; and the integrated duct has very high requirements on the position of the mounting hole, which is easy to scratch and collide with the pipeline during installation, and has poor assembly and maintenance.

[0004] To this end, a Chinese patent document with publication number CN116518159A discloses a pipeline lead-out structure, a casing and an aircraft engine, wherein the pipeline lead-out structure includes a lead-out sleeve for connecting the inside and outside of the casing and a mounting seat for mounting on the outer casing, wherein a step hole is formed through the mounting seat along the height direction; a floating ring is gap-matched in the small-diameter hole of the step hole, and a first truncated cone is convexly provided along its radial direction on the outer side of one end of the floating ring relatively above in the height direction and gap-matched in the large-diameter hole of the step hole; a cover plate for limiting the movement of the floating ring along the height direction is provided on the mounting seat; one end of the lead-out sleeve is provided on the inner casing, and the other end is gap-matched with the inner hole of the floating ring and extends to the outside of the outer casing for external pipeline connection; a first sealing rubber ring is provided between the lead-out sleeve and the inner hole of the floating ring. The present invention realizes installation compensation and compensation for the offset of the thermal expansion between the inner casing and the outer casing along the radial direction of the lead-out sleeve, and reduces the positional requirements of the mounting hole of the lead-out sleeve.

[0005] However, the pipeline lead-out structure uses a first sealing ring and a second sealing ring, but the sealing effect and service life of the sealing ring may not be ideal in a high temperature environment; multiple grooves must be processed circumferentially on the lead-out sleeve, as well as a first ring groove for installing the first sealing ring, which makes the production more complicated; in addition, one end of the lead-out sleeve is installed and fixed to an inner casing with greater vibration, resulting in the lead-out sleeve still generating greater vibration stress during actual use. Summary of the invention

[0006] In order to solve the above technical problems, the present invention provides a high-temperature and high-pressure floating bleed air sealing structure.

[0007] The present invention is achieved through the following technical solutions:

[0008] A high-temperature and high-pressure floating bleed air sealing structure comprises a combustion chamber casing, an outer duct casing, a transfer tube and a seated elbow, the combustion chamber casing is provided with an air-sealing floating mechanism, the outer duct casing is provided with an exhaust mounting seat, one end of the transfer tube is clearance-matched with the air-sealing floating mechanism, and is connected with the interior of the combustion chamber through the air-sealing floating mechanism, the other end of the transfer tube and one end of the seated elbow are jointly mounted and fixed on the exhaust mounting seat through a plurality of connecting components, and the end of the transfer tube away from the combustion chamber casing is connected with the outside through the seated elbow.

[0009] The airtight floating mechanism comprises a cabin bleed air mounting seat and a bushing assembly with a displacement ring. The cabin bleed air mounting seat is arranged on the combustion chamber casing, and the bushing assembly with a displacement ring is detachably connected to the cabin bleed air mounting seat.

[0010] The cabin bleed air mounting seat is provided with a secondary cylindrical hole, which includes a primary hole and a secondary hole arranged coaxially, the diameter of the primary hole is smaller than the diameter of the secondary hole, and the secondary hole is provided with an internal thread, and the cabin bleed air mounting seat includes an arc-shaped bottom plate and a seat body arranged on the arc-shaped bottom plate.

[0011] The bushing assembly with displacement ring includes a special nut, a displacement ring and a plug cover. The plug cover is located in the special nut, fixedly connected to the special nut, and restricts the displacement ring in the special nut. The displacement ring can float along the axial and radial directions of the special nut.

[0012] The special nut is coaxially provided with a three-stage cylindrical hole, the three-stage cylindrical hole includes a coaxial nut primary hole, a nut secondary hole and a nut tertiary hole, which are arranged in sequence and have increasing diameters in sequence. The special nut is provided with an external thread on the outer circumferential surface at the nut primary hole. The special nut is provided with a torus surface with a 100% fit with the top surface of the cabin bleed air mounting seat below the nut secondary hole. The outer circumference of the special nut is provided with an annular platform, and a plurality of grooves are provided on the annular platform in a circular array.

[0013] The displacement ring is coaxially provided with a through hole, and the displacement ring comprises a large annular platform and a small annular platform, the small annular platform is connected to the large annular platform through a cylindrical section, and the small annular platform, the cylindrical section and the large annular platform together form a flanged groove;

[0014] The plugging cover includes a cylinder and a ring arranged inside the cylinder, and the lower end face of the ring is coplanar with the lower end face of the cylinder, the cylinder is gap-matched with the nut three-level hole on the special nut, and the upper end face of the cylinder is coplanar with the upper end face of the nut three-level hole and seal-welded, the upper end of the inner hole of the ring extends axially upward to form an annular flange groove with the cylinder, and the lower end of the inner hole of the ring extends axially downward to form an annular contact surface with a fit degree of not less than 80% with the top surface of the ring table of the large annular table.

[0015] The combustion chamber casing is provided with an ear piece, the annular platform is provided with a locking wire hole, and the locking wire hole is connected with the ear piece through a steel wire to prevent the special nut from loosening.

[0016] The transfer tube comprises a thick-walled section and a thin-walled section, one end of the thin-walled section is coaxially connected with one end of the thick-walled section, and the inner diameter of the thin-walled section is consistent with the inner diameter of the thick-walled section, and a tube butterfly platform is provided on one end of the thick-walled section away from the thin-walled section, and a plurality of bolt holes are provided on the tube butterfly platform;

[0017] A chamfer R is provided at the transition between the outer circle of the thin-wall section and the outer circle of the thick-wall section;

[0018] The thin-walled section is clearance-matched with the through hole on the displacement ring.

[0019] The vacuum mounting seat comprises an arc plate and a butterfly-shaped platform arranged on the arc plate, the arc plate is provided with a plurality of rivet holes, the butterfly-shaped platform is provided with a plurality of threaded holes, and the arc plate and the butterfly-shaped platform are provided with a through hole in common.

[0020] The seated elbow comprises an elbow seat and an elbow arranged on the elbow seat, the elbow and the elbow seat are provided with an air flow channel, and the elbow seat is provided with a plurality of screw holes;

[0021] One end of the curved pipe away from the curved pipe seat is connected with a guide tube.

[0022] The connecting assembly comprises a bolt and a locking sheet sleeved on the bolt.

[0023] The beneficial effects of the present invention are:

[0024] 1. Taking advantage of the fact that the air pressure in the combustion chamber cavity is greater than the air pressure in the outer culvert flow channel and greater than the external air pressure, the high-temperature and high-pressure gas in the combustion chamber cavity is led out of the outer culvert casing through the transfer tube and the elbow with seat to achieve air bleed.

[0025] 2. By utilizing the pressure difference between the inside and outside of the combustion chamber cavity and the coordination between the various components in the floating bleed air sealing structure, sealing is achieved without the need for seals, thereby abandoning the sealing ring in the prior art, ensuring that the floating bleed air sealing structure has good sealing performance in a high temperature environment and extending its service life. At the same time, it helps to simplify the structure of the transfer tube and reduce its manufacturing cost.

[0026] 3. Since the transfer tube is not fixed to the combustion chamber casing, most of the vibrations from the engine body are effectively cut off, so that only a small part of the vibration of the whole machine is transmitted to the transfer tube, which significantly reduces the impact of vibration stress on the transfer tube.

[0027] 4. The present invention can achieve a guiding function: a chamfer R is provided at the transition point between the outer circle of the thin-wall section and the outer circle of the thick-wall section on the transition tube. When gas leaks from the combustion chamber, the chamfer R can guide the high-temperature gas to flow backward along with the outer culvert airflow, so as to protect the composite outer culvert casing.

[0028] 5. The present invention can achieve two lines of defense functions: after the special nut is threadedly connected to the cabin air bleed mounting seat installed and fixed on the combustion chamber casing, the annular surface on the special nut fits with the top surface of the cabin air bleed mounting seat to achieve sealing, preventing high-temperature gas from leaking from here, which is the first sealing defense line; when the engine is working, there is a combustion chamber airflow from front to back in the combustion chamber cavity, and there is also an outer duct airflow from front to back in the outer duct. Since the air pressure in the combustion chamber cavity is greater than the air pressure in the outer duct and greater than the air pressure in the duct, the automatic air bleed function can be achieved. At this time, the displacement ring moves in the positive direction of the Z axis under the action of the air pressure, and the top surface of the large annular table of the displacement ring fits with the annular contact surface at the bottom of the circular ring of the plug cover, thereby sealing the high-temperature and high-pressure airflow, which is the second sealing defense line.

[0029] 6. The present invention can achieve three compensation functions: first, the lower end of the transfer tube is clearance-matched with the displacement ring, so that the lower end of the transfer tube has no absolute constraint. When the transfer tube is subjected to the action of high-temperature and high-pressure gas and undergoes thermal expansion, it can freely shrink in the Z direction to reduce structural stress, thereby achieving stress compensation. Second, since the displacement ring is relatively free in all directions in space, that is, the displacement ring can move in its own radial and axial directions within a limited space, the processing deviations of the exhaust mounting seat and the cabin bleed air mounting seat can be ignored within a small range, and the transfer tube can be displacement compensated in all directions in space. Third, since the transfer tube is not fixed to the combustion chamber casing, most of the vibrations from the engine body are effectively cut off, so that only a small part of the vibration of the entire machine is transmitted to the transfer tube, thereby reducing the impact of the vibration of the entire machine, thereby achieving vibration compensation. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] Figure 1 It is a structural schematic diagram of the present invention;

[0031] Figure 2 It is a structural schematic diagram of the cabin bleed air mounting seat of the present invention;

[0032] Figure 3 A cross-sectional view of a cabin bleed air mounting seat of the present invention;

[0033] Figure 4 It is a structural schematic diagram of a bushing assembly with a displacement ring of the present invention;

[0034] Figure 5 is a cross-sectional view of a bushing assembly with a displacement ring according to the present invention;

[0035] Figure 6 for Figure 5 A local enlarged view at point A;

[0036] Figure 7 for Figure 6 A local enlarged view after the mid-gap transfer;

[0037] Figure 8 It is an assembly diagram of the plugging cover and the special nut of the present invention;

[0038] Fig. 9 It is a top view of the special nut of the present invention;

[0039] Fig.10 It is a cross-sectional view of the special nut of the present invention;

[0040] Fig.11 It is a schematic diagram of the structure of the plugging cover of the present invention;

[0041] Fig.12 is a cross-sectional view of the plugging cover of the present invention;

[0042] Fig.13 It is a structural schematic diagram of the displacement ring of the present invention;

[0043] Fig.14 is a cross-sectional view of a displacement ring of the present invention;

[0044] Fig.15 It is a schematic diagram of the structure of the transfer tube of the present invention;

[0045] Fig.16 is a cross-sectional view of the transfer tube of the present invention;

[0046] Fig.17 It is a structural schematic diagram of the air extraction mounting seat of the present invention;

[0047] Fig.18 is a cross-sectional view of the air extraction mounting seat of the present invention;

[0048] Fig.19 It is a structural schematic diagram of the elbow with seat of the present invention;

[0049] Fig. 20 It is a partial cross-sectional view of the elbow with seat of the present invention.

[0050] In the figure: 1-pipe, 2-elbow with seat, 3-bolt, 4-annular contact surface, 5-exhaust mounting seat, 6-outer casing, 7-transfer pipe, 8-blocking cover, 9-displacement ring, 10-special nut, 11-combustion chamber casing, 12-cabin bleed air mounting seat, 13-ear piece;

[0051] A1-top surface of ring platform, A2-special process surface, A3-annular surface, A4-annular contact surface, A5-annular ring, A6-cylinder, A7-external cylindrical surface;

[0052] D1-primary hole, D2-secondary hole, D3-through hole, D4-primary hole for nut, D5-secondary hole for nut, D6-third hole for nut, D7-thread lock hole, D8-gas outlet channel, D9-bolt hole, D10-through hole, D11-threaded hole, D12-rivet hole, D13-airflow channel, D14-screw hole;

[0053] e1-internal thread, e2-external thread;

[0054] G1-arc bottom plate, G2-small annular table, G3-large annular table, G4-annular table, G5-tube butterfly table, G6-seat butterfly table, G7-arc plate, G8-bend pipe seat, g1-flanging groove, g2-groove, g3-annular flanging groove;

[0055] H1-annular cavity;

[0056] K1-external flow channel, K2-cavity, K3-L-shaped cavity, K6-combustion chamber cavity;

[0057] L2-thick wall section, L3-thin wall section. DETAILED DESCRIPTION

[0058] The technical solution of the present invention is further described below, but the scope of protection claimed is not limited to the description.

[0059] like Figures 1 to 20As shown, a high-temperature and high-pressure floating bleed air sealing structure described in the present invention comprises a combustion chamber casing 11, an outer duct casing 6, a transfer tube 7 and a seated elbow 2, wherein the combustion chamber casing 11 is provided with an air-sealed floating mechanism, the outer duct casing 6 is provided with an exhaust mounting seat 5, one end of the transfer tube 7 is in clearance fit with the air-sealed floating mechanism, and is connected to the interior of the combustion chamber through the air-sealed floating mechanism, the other end of the transfer tube 7 and one end of the seated elbow 2 are fixed to the exhaust mounting seat 5 together through a plurality of connecting components, and the end of the transfer tube 7 away from the combustion chamber casing 11 is connected to the outside through the seated elbow 2. When in use, the high-temperature and high-pressure gas in the combustion chamber cavity K6 is led out of the outer duct casing 6 through the transfer tube 7 and the seated elbow 2 by utilizing the fact that the air pressure in the combustion chamber cavity K6 is greater than the air pressure in the outer duct flow channel K1 and greater than the outside air pressure, thereby achieving air bleed. By utilizing the pressure difference between the inside and outside of the combustion chamber cavity K6 and the coordination between the various components in the floating bleed air seal structure, sealing is achieved without the need for seals, and the sealing ring in the prior art is abandoned, ensuring that the floating bleed air seal structure has good sealing performance in a high temperature environment and prolongs its service life. At the same time, it helps to simplify the structure of the transfer tube 7 and reduce its manufacturing cost. One end of the transfer tube 7 is gap-matched with the air seal floating mechanism installed on the combustion chamber casing 11 to achieve a full-range floating function through the air seal floating mechanism. Since the transfer tube 7 is not fixed to the combustion chamber casing 11, most of the vibration from the engine body is effectively cut off, so that only a small part of the vibration of the whole machine is transmitted to the transfer tube 7, which significantly reduces the impact of vibration stress on the transfer tube 7.

[0060] The airtight floating mechanism comprises a cabin air bleed mounting seat 12 and a bushing assembly with a displacement ring, wherein the cabin air bleed mounting seat 12 is arranged on the combustion chamber casing 11, and the bushing assembly with a displacement ring is detachably connected to the cabin air bleed mounting seat 12. When in use, the cabin air bleed mounting seat 12 is welded to the combustion chamber casing 11.

[0061] The cabin bleed air mounting seat 12 is provided with a secondary cylindrical hole, the secondary cylindrical hole includes a primary hole D1 and a secondary hole D2 arranged coaxially, the diameter of the primary hole D1 is smaller than the diameter of the secondary hole D2, and the secondary hole D2 is provided with an internal thread e1, and the cabin bleed air mounting seat 12 includes an arc-shaped bottom plate G1 and a seat body provided on the arc-shaped bottom plate G1. When in use, the internal thread e1 on the secondary hole D2 is used to be threadedly connected with the external thread e2 on the special nut 10, so that the special nut 10 is assembled with the cabin bleed air mounting seat 12.

[0062] The bushing assembly with displacement ring includes a special nut 10, a displacement ring 9 and a plug cover 8. The plug cover 8 is located inside the special nut 10, fixedly connected to the special nut 10, and restricts the displacement ring 9 inside the special nut 10. The displacement ring 9 can float along the axial and radial directions of the special nut 10.

[0063] A three-stage cylindrical hole is coaxially provided on the special nut 10, and the three-stage cylindrical hole includes a coaxial nut primary hole D4, a nut secondary hole D5 and a nut tertiary hole D6, which are arranged in sequence and have increasing diameters. An external thread e2 is provided on the outer circumferential surface of the special nut 10 at the nut primary hole D4. A torus A3 having a 100% fit with the top surface of the cabin bleed air mounting seat 12 is provided below the nut secondary hole D5. An annular platform G4 is provided on the outer circumference of the special nut 10, and a plurality of grooves g2 are provided on the annular platform G4 in a circular array.

[0064] The displacement ring 9 is coaxially provided with a through hole D3, and the displacement ring 9 includes a large annular platform G3 and a small annular platform G2, the small annular platform G2 is connected to the large annular platform G3 through a cylindrical section, and the small annular platform G2, the cylindrical section and the large annular platform G3 together form a flange groove g1;

[0065] The plugging cover 8 includes a cylinder A6 and a ring A5 arranged inside the cylinder A6, and the lower end surface of the ring A5 is coplanar with the lower end surface of the cylinder A6, the cylinder A6 is clearance-matched with the nut tertiary hole D6 on the special nut 10, and the upper end surface of the cylinder A6 is coplanar with the upper end surface of the nut tertiary hole D6 and is seal-welded, the upper end of the inner hole of the ring A5 extends axially upward to form an annular flange groove g3 with the cylinder A6, and the lower end of the inner hole of the ring A5 extends axially downward to form an annular contact surface A4 with a fit degree of not less than 80% with the ring top surface A1 of the large annular table G3.

[0066] like Figure 8 As shown, when in use, the upper end surface of the cylinder A6 is coplanar with the upper end surface of the nut third-level hole D6 and sealed and welded, and an annular cavity H1 of unequal height is formed between the bottom surface of the ring A5 and the upper end surface of the nut first-level hole D4. The large annular platform G3 on the displacement ring 9 is assembled in the annular cavity H1, and a cavity K2 is formed between the flange groove g1 on the displacement ring 9 and the inner hole wall of the ring A5. Ensure that the height of the large annular platform G3 is less than the minimum height of the annular cavity H1, and ensure that the outer diameter of the large annular platform G3 is less than the diameter of the nut second-level hole D5 on the special nut 10, so as to form a cavity H1. Figure 5 and Figure 6 The inverted L-shaped cavity K3 shown in the figure is a variable cavity, which can be changed into Figure 7 As shown in the L-shaped cavity. Figure 5 and Figure 6 As shown, when the aircraft engine is not working, there is a gap between the top surface A1 of the ring platform on the displacement ring 9 and the annular contact surface A4 on the plug cover 8, and the cavity K2 and the L-shaped cavity K3 are two connected cavities; Figure 7As shown, when the aircraft engine is working, the top surface A1 of the ring stage on the displacement ring 9 fits with the annular contact surface A4 on the plug cover 8, and the gap is transferred to the bottom surface of the large ring stage G3 and the upper end surface of the nut primary hole D4 on the special nut 10. At this time, the cavity K2 and the L-shaped cavity K3 are separated by the displacement ring 9 and are two independent cavities. Due to the existence of the cavity K2 and the L-shaped cavity K3, the displacement ring 9 can move in its radial and axial directions within a limited space, and can be turned over within a limited space. A special process surface A2 is provided on the hole wall of the through hole D3 on the displacement ring 9 (for example, a wear-resistant coating is plated on the hole wall of the through hole D3 to form a special process surface A2) to prevent the displacement ring 9 from rubbing against the transfer tube 7. A plurality of grooves g2 are provided in a circular array on the ring stage G4 to reduce the impact of the airflow on the special nut 10 and reduce the stress on the entire structure. After the special nut 10 is assembled in place on the cabin bleed air mounting seat 12, the annular surface A3 on the special nut 10 fits with the top surface of the cabin bleed air mounting seat 12 to form a gas sealing defense line.

[0067] The combustion chamber casing 11 is provided with an ear piece 13, and the annular platform G4 is provided with a locking wire hole D7, and the locking wire hole D7 is connected with the ear piece 13 through a steel wire to prevent the special nut 10 from loosening.

[0068] The transfer tube 7 includes a thick-walled section L2 and a thin-walled section L3, one end of the thin-walled section L3 is coaxially connected to one end of the thick-walled section L2, and the inner diameter of the thin-walled section L3 is consistent with the inner diameter of the thick-walled section L2, and a tube butterfly platform G5 is provided on the end of the thick-walled section L2 away from the thin-walled section L3, and a plurality of bolt holes D9 are provided on the tube butterfly platform G5;

[0069] A chamfer R is provided at the transition point between the outer circle of the thin-walled section L3 and the outer circle of the thick-walled section L2;

[0070] The thin-walled section L3 is clearance-matched with the through hole D3 on the displacement ring 9 .

[0071] When in use, the inner hole of the transfer tube 7 is the gas outlet flow channel D8. A chamfer R is set at the transition point between the outer circle of the thin-walled section L3 and the outer circle of the thick-walled section L2 to facilitate a smooth transition of the wall thickness of the transfer tube 7. The chamfer R can change the flow direction of the high-temperature gas leaking from the clearance fit between the displacement ring 9 and the transfer tube 7 in the combustion chamber, thereby protecting the composite outer casing 6. The outer cylindrical surface A7 of the thin-walled section L3 is specially treated (for example, a wear-resistant coating is plated on the outer cylindrical surface A7) to prevent it from rubbing against the wall of the through hole D3 on the displacement ring 9. Figure 1As shown, a tube butterfly stage G5 is provided at one end of the transfer tube 7, and the tube butterfly stage G5 is fixed between the seated elbow 2 and the exhaust mounting seat 5 by bolts 3. The end of the transfer tube 7 away from the tube butterfly stage G5 is clearance-matched with the displacement ring 9, and the displacement ring 9 is restricted in the special nut 10 by the plug cover 8. The displacement ring 9 can move in the positive and negative directions of X, Y, and Z in a limited space, and the movable distance is different in each direction, and the displacement compensation of the engine pipeline can be realized. The displacement ring 9 can also be flipped around the X, Y, and Z axes respectively in the limited space. At the same time, since the end of the transfer tube 7 away from the tube butterfly stage G5 is not constrained, it can also realize the compensation of its own thermal expansion, and the double displacement compensation in this direction can be realized.

[0072] The exhaust mounting seat 5 includes an arc plate G7 and a butterfly-shaped seat G6 disposed on the arc plate G7, the arc plate G7 is provided with a plurality of rivet holes D12, the butterfly-shaped seat G6 is provided with a plurality of threaded holes D11, and the arc plate G7 and the butterfly-shaped seat G6 are provided with a through hole D10. When in use, the through hole D10 serves as a mounting channel for the transfer tube 7.

[0073] The seated elbow 2 comprises an elbow seat G8 and an elbow arranged on the elbow seat G8, an air flow channel D13 is provided on the elbow and the elbow seat G8, and a plurality of screw holes D14 are provided on the elbow seat G8;

[0074] One end of the curved pipe away from the curved pipe seat G8 is connected with a conduit 1.

[0075] The connection assembly includes a bolt 3 and a locking plate 4 sleeved on the bolt 3. After the locking plate 4 is sleeved on the bolt 3, one end of the bolt 3 is passed through the screw hole D14 on the seat elbow 2 and the bolt hole D9 on the adapter tube 7 in sequence, and then is threadedly connected and tightened with the threaded hole D11 on the exhaust mounting seat 5, so that the seat elbow 2 and one end of the adapter tube 7 are fixed to the exhaust mounting seat 5, and then the bolt 3 is prevented from loosening by using the locking plate 4.

[0076] Specifically, the high-temperature and high-pressure floating bleed air sealing structure described in the present invention can achieve one guidance, two defense lines, and three compensation functions.

[0077] One guide is: a chamfer R is provided on the transfer tube 7 at the transition point between the outer circle of the thin-walled section L3 and the outer circle of the thick-walled section L2. When gas leaks from the combustion chamber, the chamfer R can guide the high-temperature gas to flow backward along with the outer culvert airflow, so as to protect the composite outer culvert casing 6.

[0078] The two lines of defense are: after the special nut 10 is threadedly connected to the cabin bleed air mounting seat 12 fixed on the combustion chamber casing 11, the annular surface A3 on the special nut 10 fits with the top surface of the cabin bleed air mounting seat 12 to achieve sealing, preventing high-temperature gas from leaking from here, which is the first sealing line of defense; Figure 1As shown, when the engine is working, there is a combustion chamber airflow from front to back in the combustion chamber cavity K6, and there is also an outer duct airflow from front to back in the outer duct flow channel K1. Since the air pressure in the combustion chamber cavity K6 is greater than the air pressure in the outer duct flow channel K1, and greater than the air pressure in the duct 1, the automatic air bleed function can be realized. At this time, the displacement ring 9 moves in the positive direction of the Z axis under the action of the air pressure, and the top surface A1 of the large annular table G3 of the displacement ring 9 fits with the annular contact surface A4 at the bottom of the circular ring A5 of the blocking cover 8, which plays a sealing role for the high-temperature and high-pressure airflow, and serves as the second sealing defense line.

[0079] The three compensations are: Figure 1 As shown, first, the lower end of the transfer tube 7 is loosely matched with the displacement ring 9, so that the lower end of the transfer tube 7 has no absolute constraint. When the transfer tube 7 is subjected to the action of high-temperature and high-pressure gas and undergoes thermal expansion, it can freely shrink in the Z direction to reduce the structural stress, thereby achieving stress compensation. Second, since the displacement ring 9 is relatively free in all directions in space, that is, the displacement ring 9 can move in its own radial and axial directions within a limited space, the processing deviations of the exhaust mounting seat 5 and the cabin bleed air mounting seat 12 can be ignored within a small range, and the transfer tube 7 can be displacement compensated in all directions in space. Third, since the transfer tube 7 is not fixed to the combustion chamber casing 11, most of the vibrations from the engine body are effectively cut off, so that only a small part of the vibration of the entire machine is transmitted to the transfer tube 7, thereby reducing the impact of the vibration of the entire machine, thereby achieving vibration compensation.

Claims

1. A high temperature and high pressure floating bleed air sealing structure, characterized in that: The invention comprises a combustion chamber casing (11), an outer casing (6), a transfer tube (7) and a seated elbow (2); the combustion chamber casing (11) is provided with an air-sealed floating mechanism, the outer casing (6) is provided with an exhaust mounting seat (5), one end of the transfer tube (7) is clearance-matched with the air-sealed floating mechanism and is connected to the interior of the combustion chamber through the air-sealed floating mechanism, the other end of the transfer tube (7) and one end of the seated elbow (2) are fixed to the exhaust mounting seat (5) together through a plurality of connecting components, and the end of the transfer tube (7) away from the combustion chamber casing (11) is connected to the outside through the seated elbow (2).

2. The high temperature and high pressure floating bleed air seal structure according to claim 1, characterized in that: The airtight floating mechanism comprises a cabin air bleed mounting seat (12) and a bushing assembly with a displacement ring. The cabin air bleed mounting seat (12) is arranged on a combustion chamber casing (11), and the bushing assembly with a displacement ring is detachably connected to the cabin air bleed mounting seat (12).

3. The high temperature and high pressure floating bleed air seal structure according to claim 2, characterized in that: The cabin air bleed mounting seat (12) is provided with a secondary cylindrical hole, the secondary cylindrical hole comprises a primary hole (D1) and a secondary hole (D2) arranged coaxially, the diameter of the primary hole (D1) is smaller than the diameter of the secondary hole (D2), and the secondary hole (D2) is provided with an internal thread (e1); the cabin air bleed mounting seat (12) comprises an arc-shaped bottom plate (G1) and a seat body arranged on the arc-shaped bottom plate (G1).

4. The high temperature and high pressure floating bleed air seal structure according to claim 3, characterized in that: The bushing assembly with displacement ring comprises a special nut (10), a displacement ring (9) and a plug cover (8); the plug cover (8) is located inside the special nut (10), is fixedly connected to the special nut (10), and restricts the displacement ring (9) inside the special nut (10); the displacement ring (9) can float along the axial and radial directions of the special nut (10).

5. The high temperature and high pressure floating bleed air seal structure according to claim 4, characterized in that: The special nut (10) is coaxially provided with a three-stage cylindrical hole, the three-stage cylindrical hole comprising a coaxial nut primary hole (D4), a nut secondary hole (D5) and a nut tertiary hole (D6) which are arranged in sequence and have increasing diameters in sequence; the special nut (10) is provided with an external thread (e2) on the outer circumferential surface at the nut primary hole (D4); the special nut (10) is provided with a torus (A3) below the nut secondary hole (D5) with a 100% fit to the top surface of the cabin bleed air mounting seat (12); the outer circumference of the special nut (10) is provided with an annular platform (G4), and the annular platform (G4) is provided with a plurality of grooves (g2) in a circular array; The displacement ring (9) is coaxially provided with a through hole (D3), the displacement ring (9) comprises a large annular platform (G3) and a small annular platform (G2), the small annular platform (G2) is connected to the large annular platform (G3) through a cylindrical section, and the small annular platform (G2), the cylindrical section and the large annular platform (G3) together form a flange groove (g1); The plugging cover (8) comprises a cylinder (A6) and a circular ring (A5) arranged inside the cylinder (A6), and the lower end surface of the circular ring (A5) is coplanar with the lower end surface of the cylinder (A6), the cylinder (A6) is clearance-matched with the nut third-level hole (D6) on the special nut (10), and the upper end surface of the cylinder (A6) is coplanar with the upper end surface of the nut third-level hole (D6) and is sealed and welded, the upper end of the inner hole of the circular ring (A5) extends axially upward to form an annular flange groove (g3) with the cylinder (A6), and the lower end of the inner hole of the circular ring (A5) extends axially downward to form an annular contact surface (A4) with a fitting degree of not less than 80% with the ring top surface (A1) of the large ring stage (G3).

6. The high temperature and high pressure floating bleed air seal structure according to claim 5, characterized in that: The combustion chamber casing (11) is provided with an ear piece (13), the annular platform (G4) is provided with a locking wire hole (D7), and the locking wire hole (D7) is connected to the ear piece (13) through a steel wire to prevent the special nut (10) from loosening.

7. The high temperature and high pressure floating bleed air seal structure according to claim 5, characterized in that: The transfer tube (7) comprises a thick-walled section (L2) and a thin-walled section (L3), one end of the thin-walled section (L3) is coaxially connected to one end of the thick-walled section (L2), and the inner diameter of the thin-walled section (L3) is consistent with the inner diameter of the thick-walled section (L2); a tube butterfly platform (G5) is provided on the end of the thick-walled section (L2) away from the thin-walled section (L3), and a plurality of bolt holes (D9) are provided on the tube butterfly platform (G5); A chamfer R is provided at the transition point between the outer circle of the thin-walled section (L3) and the outer circle of the thick-walled section (L2); The thin-walled section (L3) is clearance-matched with the through hole (D3) on the displacement ring (9).

8. The high temperature and high pressure floating bleed air seal structure according to claim 1, characterized in that: The air extraction mounting seat (5) comprises an arc plate (G7) and a butterfly-shaped seat (G6) arranged on the arc plate (G7); the arc plate (G7) is provided with a plurality of rivet holes (D12); the butterfly-shaped seat (G6) is provided with a plurality of threaded holes (D11); and the arc plate (G7) and the butterfly-shaped seat (G6) are jointly provided with a through hole (D10).

9. The high temperature and high pressure floating bleed air seal structure according to claim 1, characterized in that: The seated bent pipe (2) comprises a bent pipe seat (G8) and a bent pipe arranged on the bent pipe seat (G8); an air flow channel (D13) is provided on the bent pipe and the bent pipe seat (G8); and a plurality of screw holes (D14) are provided on the bent pipe seat (G8); One end of the curved pipe away from the curved pipe seat (G8) is connected with a guide tube (1).

10. The high temperature and high pressure floating bleed air seal structure according to claim 1, characterized in that: The connection assembly comprises a bolt (3) and a locking plate (4) sleeved on the bolt (3).

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