A whole turbine outer ring, its mounting structure and an aero-engine with the same

Abstract

The application provides a whole turbine outer ring, an installation structure thereof and an aero-engine with the same, and belongs to the technical field of aero-engines.The whole turbine outer ring comprises an outer ring body and a clamping part on the outer ring body; the clamping part is integrally formed on the outer circumferential surface of the outer ring body and is arranged outward along the radial direction of the outer ring body; the clamping part is provided with a first clamping surface and a second clamping surface for axial limiting, and is also provided with a third clamping surface and a fourth clamping surface for circumferential limiting; in the application, the outer ring body is set as a whole outer ring body, so that the deformation of the whole turbine outer ring is consistent when the outer ring body is subjected to thermal expansion deformation, and the thermal stress caused by thermal expansion cannot be completely released, and meanwhile, the clamping part on the outer ring body is used for mounting the whole turbine outer ring to an external device, so that axial and radial limiting is realized.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aero-engines, in particular to a whole turbine outer ring, an installation structure thereof and an aero-engine with the same. BACKGROUND

[0002] The aero-engine comprises a turbine casing, turbine blades, stator blades and a turbine outer ring.

[0003] With the development of aero-engines, the requirements for performance parameters thereof are increasingly strict, and the turbine inlet temperature is also increasing. The turbine inlet temperature of the current gas turbine engine and ground gas turbine is as high as 1600-2000K, which poses a severe challenge to the reliable application of turbine blades, stator blades, turbine outer rings and other parts directly contacted with high-temperature and high-pressure gas. The gas turbine outer ring is a special stator part, which not only needs to resist the erosion of gas, but also needs to ensure its centering and positioning in such a harsh environment, and there should be a suitable tip clearance between the turbine blades, which requires the turbine outer ring to have high-temperature resistance, uniform thermal expansion and reliable connection structure.

[0004] The gas turbine outer ring in the prior art is generally made of high-temperature alloy metal, and has a circumferential segmented structure. The segmented turbine outer ring is hung on the ring groove of the metal outer casing through a hook structure, and the thermal stress caused by the incoordination of thermal deformation cannot be completely released when the turbine outer ring is subjected to thermal deformation, at this time, the high-temperature and high-pressure gas will leak from the circumferential gap between the turbine outer rings, causing ablation to the turbine casing. SUMMARY

[0005] Therefore, the technical problem to be solved by the present application is that in the connection between the segmented turbine outer ring and the turbine casing in the prior art, the thermal deformation of the turbine casing and the turbine outer ring does not match, resulting in inconsistent gap between the turbine blades and the turbine outer ring, so that a whole turbine outer ring, an installation structure thereof and an aero-engine with the same are provided.

[0006] In order to solve the above technical problems, the present application provides a whole turbine outer ring, comprising: an outer ring body; a clamping part integrally formed on the outer circumferential surface of the outer ring body and protruding outward along the radial direction of the outer ring body; the clamping part has a first clamping surface and a second clamping surface for axial limiting, and also has a third clamping surface and a fourth clamping surface for circumferential limiting.

[0007] Preferably, the first clamping surface and the second clamping surface are perpendicular to the axial direction of the outer ring body.

[0008] Preferably, the second clamping surface and the third clamping surface are perpendicular to the circumferential direction of the outer ring body.

[0009] Preferably, the clamping portion comprises: an annular flange arranged along the circumference of the outer ring body, the front and back sides of the annular flange forming the first clamping surface and the second clamping surface; a plurality of grooves are arranged on the annular flange along the circumference and are spaced apart, the left and right sides of the grooves forming the third clamping surface and the fourth clamping surface.

[0010] Preferably, the clamping portion comprises: a plurality of protrusions arranged along the circumference of the outer ring body, the front and back sides of the protrusions forming the first clamping surface and the second clamping surface, and the left and back sides of the protrusions forming the third clamping surface and the fourth clamping surface.

[0011] Preferably, an installation structure of the integral turbine outer ring is also provided, which is used for installing the integral turbine outer ring of any of the above-mentioned solutions, and comprises: an outer casing; an inner casing connected with the outer casing, and the inner casing and the outer casing form an annular accommodating cavity for installing the integral turbine outer ring; a circumferential limiting ring installed between the outer casing and the inner casing, the circumferential limiting ring has a circumferential clamping structure extending towards the annular accommodating cavity, and the circumferential clamping structure comprises: a third clamping jaw and a fourth clamping jaw matched with each other, the third clamping jaw is used for abutting against the third clamping surface of the clamping portion of the integral turbine outer ring, and the fourth clamping jaw is used for abutting against the fourth clamping surface of the clamping portion of the integral turbine outer ring; an axial limiting ring arranged between the outer casing and the inner casing, the axial limiting ring has a first clamping jaw extending towards the annular accommodating cavity and having elasticity, and the first clamping jaw is used for abutting against the first clamping surface of the clamping portion of the integral turbine outer ring; the outer casing has a second clamping jaw matched with the first clamping jaw, and the second clamping jaw is used for abutting against the second clamping surface of the clamping portion of the integral turbine outer ring.

[0012] Preferably, the third clamping jaw is a rigid support, the fourth clamping jaw is an elastic support, and the direction in which the third clamping jaw abuts against the third clamping surface is opposite to the stress direction of the integral turbine outer ring in use.

[0013] Preferably, the fourth clamping jaw has an arc structure.

[0014] Preferably, after the integral turbine outer ring is installed, a cooling channel for passing cooling gas is formed between the inner casing and the outer side wall of the integral turbine outer ring, the outer casing has a gas inlet for the cooling gas to enter, the inner casing has a gas outlet for the cooling gas to be discharged, and the cooling gas enters the cooling channel from the gas inlet and is discharged from the gas outlet.

[0015] Preferably, the gas inlet has a double-layer structure, a buffer cavity is formed between the two side gas inlets, the inlet of the buffer cavity is a first gas inlet, the outlet of the buffer cavity is a second gas inlet, and the gas inlet cross-sectional area of the second gas inlet is smaller than that of the first gas inlet.

[0016] Preferably, the second gas inlet has a plurality of gas inlets arranged at intervals, and the total gas inlet cross-sectional area of the plurality of second gas inlets is smaller than that of the first gas inlet.

[0017] Preferably, the first clamping jaw of the axial limiting ring is an annular whole structure, and a plurality of air holes for air ventilation are formed on the first clamping jaw.

[0018] Preferably, the second clamping jaw on the outer casing is an annular baffle extending towards the center direction, and a plurality of air outlets for air outlet are formed on the annular baffle.

[0019] In addition, an aero-engine is also provided, which comprises the integral turbine outer ring according to any one of the above solutions or the mounting structure of the integral turbine outer ring according to any one of the above solutions.

[0020] The technical solutions of the present application have the following advantages:

[0021] 1. The integral turbine outer ring provided by the present application is provided with an integral outer ring body, so that the deformation of the outer ring body is coordinated and consistent when the outer ring body is subjected to thermal expansion deformation, and the thermal stress caused by thermal expansion cannot be completely released. Meanwhile, the clamping part on the outer ring body is used to mount the integral turbine outer ring on an external device, so that axial and radial limiting is realized.

[0022] 2. The mounting structure of the integral turbine outer ring provided by the present application is provided with a rigid third clamping jaw abutting against a third clamping surface of the turbine outer ring to limit the circumferential force generated by the turbine outer ring during operation, and a flexible fourth clamping jaw capable of abutting against a fourth clamping surface to limit the other side of the turbine outer ring in the circumferential direction and provide elastic force, so that the turbine outer ring is always in abutment with the third clamping jaw and the fourth clamping jaw.

[0023] 3. The aero-engine provided by the present application is provided with the integral turbine outer ring, and the turbine outer ring is integral, so that the installation is simpler, and the deformation of the turbine outer ring is more coordinated when subjected to thermal expansion deformation. The mounting structure of the integral turbine outer ring is used in the aero-engine to limit the turbine outer ring in the axial and circumferential directions, center the turbine outer ring, cool the turbine outer ring and prevent high-temperature and high-pressure gas from backflowing. BRIEF DESCRIPTION OF DRAWINGS

[0024] In order to more clearly illustrate the specific embodiments of the present application or the technical solutions in the prior art, the drawings needed in the following specific embodiments or prior art description will be briefly introduced. Obviously, the drawings in the following description are some embodiments of the present application, and other drawings can be obtained by those skilled in the art without creative labor.

[0025] Figure 1 A front view of a specific embodiment of the aero-engine of the present application is provided.

[0026] Figure 2 AFigure 1 A schematic view of cold air flow in the mounting structure of the integral turbine outer ring in

[0027] Figure 3 A schematic view of cold air flow in the mounting structure of the integral turbine outer ring in Figure 1 A partial enlarged view of the clamping portion of the turbine outer ring cooperating with the circumferential limiting ring in one embodiment of

[0028] Figure 4 A schematic view of cold air flow in the mounting structure of the integral turbine outer ring in Figure 1 A front side perspective view of the turbine outer ring with protrusions in

[0029] Figure 5 A schematic view of cold air flow in the mounting structure of the integral turbine outer ring in Figure 4 An enlarged view of A in

[0030] Figure 6 A schematic view of cold air flow in the mounting structure of the integral turbine outer ring in Figure 1 A rear side perspective view of the turbine outer ring with protrusions in

[0031] Figure 7 A schematic view of cold air flow in the mounting structure of the integral turbine outer ring in Figure 6 An enlarged view of B in

[0032] Figure 8 A schematic view of cold air flow in the mounting structure of the integral turbine outer ring in Figure 1 A partial enlarged view of the clamping portion of the turbine outer ring with protrusions cooperating with the circumferential limiting ring in another embodiment of

[0033] Figure 9 A schematic view of cold air flow in the mounting structure of the integral turbine outer ring in Figure 1 A partial view of the annular flange of the turbine outer ring cooperating with the circumferential limiting ring in

[0034] Figure 10 A schematic view of cold air flow in the mounting structure of the integral turbine outer ring in Figure 1 A front side perspective view of the turbine outer ring with annular flange in

[0035] Figure 11 Figure 10 An enlarged view of C in

[0036] Figure 12 A rear side perspective view of the turbine outer ring with annular flange in

[0037] Figure 13 A schematic view of cold air flow in the mounting structure of the integral turbine outer ring in Figure 12 An enlarged view of D in

[0038] Figure 14 A schematic view of cold air flow in the mounting structure of the integral turbine outer ring in Figure 1 A partial enlarged view of the circumferential limiting ring cooperating with the groove of the turbine outer ring in one embodiment of

[0039] BRIEF DESCRIPTION OF REFERENCE NUMERALS:

[0040] 1, outer ring body; 2, clamping part; 3, first clamping surface; 4, second clamping surface; 5, third clamping surface; 6, fourth clamping surface; 7, groove; 8, outer casing; 9, inner casing; 10, circumferential limiting ring; 11, third clamping jaw; 12, fourth clamping jaw; 13, axial limiting ring; 14, first clamping jaw; 15, second clamping jaw; 16, cooling channel; 17, buffer cavity; 18, first air inlet; 19, second air inlet; 20, air hole; 21, air outlet. DETAILED DESCRIPTION

[0041] The technical solutions of the present application will be described clearly and completely below in conjunction with the drawings. Obviously, the described embodiments are part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative labor fall within the scope of protection of the present application.

[0042] In the description of the present application, it should be noted that the orientations or positional relationships indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. are based on the orientations or positional relationships shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, and therefore cannot be understood as indicating or implying that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as limiting the present application. In addition, the terms "first", "second", "third" are only for descriptive purposes and cannot be understood as indicating or implying relative importance.

[0043] In the description of the present application, it should be noted that unless otherwise explicitly specified and limited, the terms "mounting", "connection", "connection" should be understood broadly, for example, it can be fixedly connected, or it can be detachably connected, or integrally connected; it can be mechanically connected, or it can be electrically connected; it can be directly connected, or it can be indirectly connected through an intermediate medium; it can be the communication inside two elements. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0044] In addition, the technical features involved in the different embodiments of the present application described below can be combined with each other as long as they do not conflict with each other.

[0045] The present embodiment provides an aero-engine, in particular a gas turbine engine, which has a one-piece turbine outer ring mounted on the tail of the aero-engine by a mounting structure.

[0046] As Figure 1As shown in the figure, it is a front view of a specific embodiment of the aero-engine provided by the embodiment, and the lower half of the structure is omitted because the whole aero-engine is a hollow cylinder. In the aero-engine provided by the embodiment, an integral turbine outer ring and a mounting structure for mounting the integral turbine outer ring are included. In the high-temperature working process of high-temperature and high-pressure gas, the thermal expansion of the integral turbine outer ring is small; and when thermal deformation occurs, the gap between the integral turbine outer ring and the turbine blade is consistent, which can prevent the problem of leakage of high-temperature and high-pressure gas from the circumferential gap between the turbine outer ring.

[0047] As shown in the figure, it is a front view of a specific embodiment of the aero-engine provided by the embodiment, and the lower half of the structure is omitted because the whole aero-engine is a hollow cylinder. In the aero-engine provided by the embodiment, an integral turbine outer ring and a mounting structure for mounting the integral turbine outer ring are included. In the high-temperature working process of high-temperature and high-pressure gas, the thermal expansion of the integral turbine outer ring is small; and when thermal deformation occurs, the gap between the integral turbine outer ring and the turbine blade is consistent, which can prevent the problem of leakage of high-temperature and high-pressure gas from the circumferential gap between the turbine outer ring. Figures 5 to 8 As shown in the figure, it is a specific embodiment of the integral turbine outer ring provided by the embodiment, which includes an outer ring body 1, which is an integral structure of a rotating body structure rotating around the axis; and a clamping part 2 provided on the outer ring body 1 for fixed connection with external devices. The clamping part 2 is integrally formed with the outer ring body 1 and protrudes outwardly along the radial direction of the outer ring body 1 on the outer peripheral surface of the outer ring body 1; the clamping part 2 has a first clamping surface 3 and a second clamping surface 4 for axial limiting, and also has a third clamping surface 5 and a fourth clamping surface 6 for circumferential limiting. By setting the outer ring body 1 as an integral outer ring body 1, the deformation of the whole outer ring body 1 is coordinated and consistent when thermal expansion deformation occurs, which reduces the defect that the thermal stress caused by thermal expansion cannot be completely released, and the clamping part 2 on the outer ring body 1 mounts the integral turbine outer ring on the external device to realize axial and radial limiting.

[0048] It should be noted that the outer ring body 1 is made of ceramic matrix composite material, which is a water-soluble polymer compound chemically modified from natural cellulose, and can withstand higher temperature.

[0049] As shown in the figure, it is a specific embodiment of the integral turbine outer ring provided by the embodiment, which includes an outer ring body 1, which is an integral structure of a rotating body structure rotating around the axis; and a clamping part 2 provided on the outer ring body 1 for fixed connection with external devices. The clamping part 2 is integrally formed with the outer ring body 1 and protrudes outwardly along the radial direction of the outer ring body 1 on the outer peripheral surface of the outer ring body 1; the clamping part 2 has a first clamping surface 3 and a second clamping surface 4 for axial limiting, and also has a third clamping surface 5 and a fourth clamping surface 6 for circumferential limiting. By setting the outer ring body 1 as an integral outer ring body 1, the deformation of the whole outer ring body 1 is coordinated and consistent when thermal expansion deformation occurs, which reduces the defect that the thermal stress caused by thermal expansion cannot be completely released, and the clamping part 2 on the outer ring body 1 mounts the integral turbine outer ring on the external device to realize axial and radial limiting. Figure 5 Figure 7 Figure 11 Figure 13 As shown in the figure, it is an embodiment of the integral turbine outer ring provided by the embodiment, the first clamping surface 3 and the second clamping surface 4 are perpendicular to the axial direction of the outer ring body 1, which limits the axial movement of the clamping part 2 and thus limits the axial displacement of the outer ring body 1. Since the first clamping surface 3 and the second clamping surface 4 are perpendicular to the axial direction of the outer ring body 1, the axial limiting of the clamping part 2 is more secure. In addition, as an alternative embodiment, the first clamping surface 3 and the second clamping surface 4 can also be inclined, for example, tapered or trapezoidal surfaces, which can also limit the axial movement of the outer ring body 1.

[0050] As shown in the figure, it is an embodiment of the integral turbine outer ring provided by the embodiment, the first clamping surface 3 and the second clamping surface 4 are perpendicular to the axial direction of the outer ring body 1, which limits the axial movement of the clamping part 2 and thus limits the axial displacement of the outer ring body 1. Since the first clamping surface 3 and the second clamping surface 4 are perpendicular to the axial direction of the outer ring body 1, the axial limiting of the clamping part 2 is more secure. In addition, as an alternative embodiment, the first clamping surface 3 and the second clamping surface 4 can also be inclined, for example, tapered or trapezoidal surfaces, which can also limit the axial movement of the outer ring body 1. Figure 5 Figure 7 Figure 11 Figure 13 ​​​​​​As shown, the third clamping surface 5 and the fourth clamping surface 6 are perpendicular to the circumference of the outer ring body 1, and after being perpendicular to the circumference, the circumferential displacement of the third clamping surface 5 and the fourth clamping surface 6 is limited, thereby limiting the circumferential movement of the outer ring body 1. In addition, as an alternative embodiment, the third clamping surface 5 and the fourth clamping surface 6 can also be inclined, for example, tapered or trapezoidal surfaces, etc., which can also limit the circumferential movement of the outer ring body 1. In the integral turbine outer ring, the axial restriction of the outer ring body 1 can be clamped onto the first clamping surface 3 and the second clamping surface 4 by a single part, or the axial movement of the outer ring body 1 can be restricted by two parts abutting onto the first clamping surface 3 and the second clamping surface 4, and the present embodiment does not limit it. The circumferential restriction of the outer ring body 1 can be provided with two clamping jaws by a single part, and the two clamping jaws abut onto the third clamping surface 5 and the fourth clamping surface 6, respectively.

[0051] It should be noted that the present embodiment does not limit the specific structure of the clamping portion 2, as long as it has the first clamping surface 3 and the second clamping surface 4 for axial positioning, and the third clamping surface 5 and the fourth clamping surface 6 for circumferential positioning. For example, it can be several protrusions arranged along the circumference of the outer ring body 1 as shown in Figures 3-8 which are used for axial positioning and circumferential positioning; it can also be as shown in Figures 9-14 a ring-shaped flange is arranged along the circumference of the outer ring body 1, and the ring-shaped flange is used for axial positioning, and a plurality of recesses 7 for circumferential positioning are arranged on the ring-shaped flange.

[0052] As shown in Figures 9 to 14As shown, another specific embodiment of the integral turbine outer ring provided in this embodiment is illustrated. The locking part 2 includes an annular flange arranged circumferentially along the outer ring body 1, the radial cross-section of which is circular. A first locking surface 3 and a second locking surface 4 are formed on the two axial sides of the annular flange. A plurality of grooves 7 are spaced circumferentially on the annular flange, and a third locking surface 5 and a fourth locking surface 6 are formed on the two opposite sides of the grooves 7. In this case, the locking part 2 is an annular flange protruding radially outward, with grooves 7 arranged radially inward on the annular flange, the grooves 7 penetrating axially. By restricting the first locking surface 3 and the second locking surface 4 of the annular flange, the axial displacement of the turbine outer ring is restricted; by restricting the third locking surface 5 and the fourth locking surface 6 of the annular flange, the circumferential displacement of the turbine outer ring is restricted. Alternatively, as an alternative embodiment, the grooves 7 may not penetrate axially. Alternatively, as an alternative embodiment, the annular flange may not be provided, and the outer ring body 1 may be limited by locking the two end faces along the axis of the outer ring body 1. When engaging the annular flange, the first engaging surface 3 and the second engaging surface 4 of the annular flange abut against each other on both sides in the axial direction; in the circumferential direction, they abut against the opposing third engaging surface 5 and fourth engaging surface 6 within the groove 7. Specifically, the outer ring body 1 is a single ring, and single ring parts can be used to abut against the first engaging surface 3 and the second engaging surface 4 respectively. The first engaging surface 3 and the second engaging surface 4 are abutted and limited within each groove 7, thus restricting the outer ring body 1 in both the axial and circumferential directions.

[0053] like Figures 3 to 8 As shown, this embodiment provides one implementation of the integral turbine outer ring. The locking part 2 includes: a plurality of protrusions spaced circumferentially along the outer ring body 1, and a plurality of protrusions arranged in a circumferential array around the center of the outer ring body 1. The front and rear sides of the protrusions form a first locking surface 3 and a second locking surface 4, and the left and rear sides of the protrusions form a third locking surface 5 and a fourth locking surface 6. The protrusions are plate-like structures, and the protrusions are arranged in a circumferential array around the center of the outer ring body 1 on the outer circumferential surface of the outer ring body 1. In addition, as an alternative implementation, two adjacent protrusions are staggered by a certain distance in the axial direction. In addition, as an alternative implementation, the protrusions may not be provided, and the outer ring body 1 is limited by locking the two end faces of the outer ring body 1 along the axis. When a plurality of protrusions are spaced circumferentially along the outer ring body 1, the first locking surface 3 and the second locking surface 4 of each protrusion in the axial direction are abutted and limited, thereby preventing the outer ring body 1 from moving in the axial direction. The third and fourth engagement surfaces 5 and 6 in the circumferential direction of the protrusion are also engaged and restricted, thus restricting the rotation of the outer ring body 1 in the circumferential direction.

[0054] like Figure 1 , Figure 3 , Figure 9As shown, an integral turbine outer ring mounting structure is also provided for mounting the aforementioned integral turbine outer ring, including: an outer casing 8 and an inner casing 9; both the outer casing 8 and the inner casing 9 are annular integral structures, and the inner casing 9 is connected to the outer casing 8 by bolts. An annular receiving cavity for mounting the integral turbine outer ring is formed between the inner casing 9 and the outer casing 8; the circumferential limiting ring 10 is a rotating structure, and after being clamped by the outer casing 8 and the inner casing 9, the circumferential limiting ring 10 passes through the outer casing 8, the circumferential limiting ring 10 and the inner casing 9 in sequence by bolts, and the bolts fix the circumferential limiting ring 10 and the inner casing 9 to the outer casing 8. The circumferential limiting ring 10 has a circumferential snap-fit ​​structure extending toward the annular receiving cavity, that is, extending radially inward. The circumferential locking structure includes a third locking jaw 11 and a fourth locking jaw 12 that cooperate with each other. The third locking jaw 11 is used to abut against the third locking surface 5 of the locking part 2 of the integral turbine outer ring, and the fourth locking jaw 12 is used to abut against the fourth locking surface 6 of the locking part 2 of the integral turbine outer ring. An axial limiting ring 13 is disposed between the outer casing 8 and the inner casing 9. The axial limiting ring 13 is a rotating body structure with a certain elasticity in the axial direction. Its axial direction is limited by the inner casing 9 and the circumferential limiting ring 10, respectively. Its radial direction is formed by the top circumferential surface cooperating with the circumferential surface of the inner casing 9 to form a precision clearance to ensure centering. The axial limiting ring 13 has a first elastic pawl 14 extending toward the annular receiving cavity, the first pawl 14 being used to abut against the first engagement surface 3 of the engagement portion 2 of the integral turbine outer ring; the outer casing 8 has a second pawl 15 for cooperating with the first pawl 14, the second pawl 15 being used to abut against the second engagement surface 4 of the engagement portion 2 of the integral turbine outer ring.

[0055] like Figure 3 , Figure 9 As shown, this is one embodiment of the integral turbine outer ring provided in this example. When the third claw 11 abuts against the third engagement surface 5, the third claw 11 provides rigid support. The third claw 11 is a cuboid structure extending radially towards the groove 7. A section of the cuboid structure extends towards the third engagement surface 5, and the abutting block abuts against the third engagement surface 5. Because the direction in which the third claw 11 abuts against the third engagement surface 5 is directly opposite to the rotation direction of the working blade, when the blade is in operation, the blade tip clearance is small. When the blade scrapes against the outer ring body 1, the third claw 11 provides a certain amount of shock absorption and buffering for the turbine outer ring. The fourth claw 12 provides elastic support. When it abuts against the fourth engagement surface 6, because the abutting direction of the fourth claw 12 is opposite to the rotation direction of the working blade, the fourth claw 12 only needs the elastic force generated by its elastic deformation to abut against the fourth engagement surface 6 of the column engagement part 2, thus providing circumferential limiting. Alternatively, as an alternative implementation, the third claw 11 may be of other shapes extending radially into the groove 7, such as a triangle or trapezoid.

[0056] like Figure 3 , Figure 9As shown in the drawings, the fourth clamping jaw 12 is in an arc structure, and has a certain elastic force when abutting, thereby achieving circumferential limiting. Alternatively, the fourth clamping jaw 12 can be provided in an L-shaped flexible structure, or an elliptical arc structure, etc. Figure 8 , Figure 14 The L-shaped flexible structure or the elliptical arc structure, etc. can be used.

[0057] As shown in the drawings, the fourth clamping jaw 12 is in an arc structure, and has a certain elastic force when abutting, thereby achieving circumferential limiting. Alternatively, the fourth clamping jaw 12 can be provided in an L-shaped flexible structure, or an elliptical arc structure, etc. Figure 1 , Figure 2 As shown in the drawings, the fourth clamping jaw 12 is in an arc structure, and has a certain elastic force when abutting, thereby achieving circumferential limiting. Alternatively, the fourth clamping jaw 12 can be provided in an L-shaped flexible structure, or an elliptical arc structure, etc.

[0058] As shown in the drawings, the fourth clamping jaw 12 is in an arc structure, and has a certain elastic force when abutting, thereby achieving circumferential limiting. Alternatively, the fourth clamping jaw 12 can be provided in an L-shaped flexible structure, or an elliptical arc structure, etc. Figure 1 As shown in the drawings, the fourth clamping jaw 12 is in an arc structure, and has a certain elastic force when abutting, thereby achieving circumferential limiting. Alternatively, the fourth clamping jaw 12 can be provided in an L-shaped flexible structure, or an elliptical arc structure, etc.

[0059] As shown in the drawings, the fourth clamping jaw 12 is in an arc structure, and has a certain elastic force when abutting, thereby achieving circumferential limiting. Alternatively, the fourth clamping jaw 12 can be provided in an L-shaped flexible structure, or an elliptical arc structure, etc. Figure 1As shown, this embodiment provides one implementation of the integral turbine outer ring. The second air inlet 19 has two rows spaced apart, each row arranged in a circular array around the center of the inner casing 9. This embodiment has two rows of second air inlets 19. The second air inlets 19 communicate with the buffer chamber 17, and the outlet direction of the second air inlets 19 faces the outer ring body 1. The total intake cross-sectional area of ​​the multiple second air inlets 19 is smaller than the intake cross-sectional area of ​​the first air inlet 18, causing the cold air to be compressed within the buffer chamber 17. This increases the flow rate of the cold air entering the cooling channel 16 from the second air inlets 19, enhancing the cooling effect. Alternatively, as an alternative implementation, the second air inlets 19 can be configured with multiple rows, such as three or four rows. Furthermore, as an alternative implementation, the total intake area of ​​the second air inlets 19 can be equal to the intake cross-sectional area of ​​the first air inlet 18, while still achieving a cooling effect.

[0060] like Figure 1 As shown, this embodiment provides one implementation of the integral turbine outer ring. The first claw 14 of the axial limiting ring 13 is an integral ring structure. The annular axial limiting ring 13 can provide more axial support force. The first claw 14 has several vent holes 20 for ventilation. The cold air coming out of the cooling channel 16 passes through the vent holes 20, preventing high-temperature and high-pressure combustion gas from flowing back into the cooling channel 16. In addition, as an alternative implementation, the first claw 14 of the axial limiting ring 13 is a circumferential array with multiple claws spaced apart. In this case, the cold air can flow through the gap between two adjacent first claws 14.

[0061] like Figure 1 As shown, this embodiment provides one implementation of the integral turbine outer ring. The second claw 15 on the outer casing 8 is an annular baffle extending towards the center. The annular baffle abuts against one side of the turbine outer ring to provide axial support. The annular baffle has several air outlets 21 for air discharge. The cold air coming out of the vent 20 flows through the several air outlets 21 to the high-temperature and high-pressure combustion gas side, preventing the high-temperature and high-pressure combustion gas from backflowing from the annular baffle. Alternatively, as an alternative implementation, an axial limiting ring 13 can be provided between the outer casing 8 and the circumferential limiting ring 10, so that the turbine outer ring is axially limited by the two opposing axial limiting rings 13.

[0062] Installation method of the integral turbine outer ring: The outer casing 8 is a rotating body structure that rotates around the corresponding axis. It is bolted to the circumferential elastic ring and the inner casing 9. The outer casing 8 extends an annular baffle towards the center and limits its axial movement by abutting against the second engagement surface 4 of the turbine outer ring. The circumferential limiting ring 10 has a third claw 11 and a fourth claw 12. The third claw 11 abuts against the third engagement surface 5 of the groove 7 or boss of the turbine outer ring. It has a large thickness and high rigidity, so that the outer ring body 1 can only produce a small elastic deformation along the circumferential direction. At the same time, the fourth claw 12 abuts against the fourth engagement surface 6 of the boss or groove 7. The fourth claw 12 is arc-shaped and only needs to generate elastic force to perform the circumferential limiting function. The number of third claws 11 and fourth claws 12 is the same as the number of bosses or grooves 7. The outer ring body 1 is a complete annular structure with a T-shaped cross-section. Viewed along the axis, the outer surface of the turbine outer ring has multiple bosses or annular flanges, which are used to form a circumferential radial fit with the circumferential limiting ring 10. Axial limiting of the turbine outer ring is achieved by the axial limiting ring 13 and the annular baffle pressing against each other. The axial limiting ring 13 and the annular baffle abut against the first and second engagement surfaces 3 and 4 of the engagement portion 2 of the outer ring body 1. The annular baffle is integral with the outer casing 8. The impact cooling structure on the inner casing 9 is divided into three layers: the top layer has a first air inlet 18, the middle layer is a buffer chamber 17, and the bottom layer has a second air inlet 19. Cool air enters the buffer chamber 17 from the first air inlet. Because the intake cross-sectional area of ​​the first air inlet 18 is larger than that of the second air inlet 19, the gas is pressurized in the buffer chamber 17 and then enters the upper part of the turbine outer ring through the second air inlet 19.

[0063] like Figure 2 The diagram illustrates airflow: Secondary cool air from the engine enters the buffer chamber 17 through the first intake port 18 of the inner casing 9. Since the intake cross-sectional area of ​​the first intake port 18 is larger than that of the second intake port 19, the air is pressurized within the buffer chamber 17 and forced into the second intake port 19, entering the cooling channel 16. The cool air first impacts the upper surface of the outer ring. Simultaneously, because the effective area of ​​the axial limiting ring 13 is smaller than that of the second intake port 19, the cool air is collected and pressurized above the turbine outer ring, preventing backflow of combustion gases from the gaps. Another portion of the cool air passes through the vent 20 of the axial limiting ring 13 to further cool the circumferential limiting ring 10 and the annular baffle, and then exits from the outlet 21 of the annular baffle, preventing backflow of combustion gases at the annular baffle.

[0064] The working principle of the integral turbine outer ring is as follows: the application mainly comprises an outer casing 8, a circumferential limiting ring 10, a turbine outer ring, an axial limiting ring 13 and an inner casing 9, the circumferential limiting ring 10 and the inner casing 9 are fixed to the outer casing 8 through bolts, the axial limiting ring 13 is arranged in an annular accommodating cavity formed by the inner casing 9 and the outer casing 8, and the axial limiting ring 13 and the circumferential limiting ring 10 jointly limit and fix the turbine outer ring. The third clamping jaw 11 and the fourth clamping jaw 12 of the circumferential limiting ring 10 are respectively clamped to the third clamping surface 5 and the fourth clamping surface 6 on the protrusion or the recess 7 of the turbine outer ring, so as to limit the turbine outer ring in the radial direction. The first clamping jaw 14 and the second clamping jaw 15 of the axial elastic ring limit the turbine outer ring in the axial direction. The first clamping jaw 14 is arranged on the axial limiting ring 13, the second clamping jaw 15 is an annular baffle arranged on the outer casing 8, the first clamping jaw 14 is abutted to the first clamping surface 3 of the clamping part 2 of the turbine outer ring, the second clamping jaw 15 is abutted to the second clamping surface 4 of the clamping part 2 of the turbine outer ring, so as to limit the turbine outer ring in the axial direction. Cold air enters the buffer cavity 17 from the first air inlet 18 on the inner casing 9, then is pressurized and discharged to the cooling channel 16 from the second air inlet 19, so as to cool the turbine outer ring and prevent high-temperature and high-pressure gas from backflowing.

[0065] Obviously, the above embodiments are only examples for clearly illustrating the application, and are not intended to limit the application. Based on the above description, other different forms of changes or variations can be made by those skilled in the art. All the embodiments do not need to be enumerated, and the obvious changes or variations derived therefrom are still within the protection scope of the application.

Claims

1. An installation structure of an integral turbine outer ring, characterized by, The application relates to a mounting structure for a whole turbine outer ring, which comprises an outer ring body (1); A clamping part (2) is integrally formed on the outer circumferential surface of the outer ring body (1) and protrudes radially outward; The clamping part (2) is provided with a first clamping surface (3) and a second clamping surface (4) for axial positioning, and is also provided with a third clamping surface (5) and a fourth clamping surface (6) for circumferential positioning; The mounting structure comprises: An outer casing (8); An inner casing (9) connected with the outer casing (8), and an annular accommodating cavity for mounting the whole turbine outer ring is formed between the outer casing (8) and the inner casing (9); A circumferential limiting ring (10) is mounted between the outer casing (8) and the inner casing (9), and the circumferential limiting ring (10) is provided with a circumferential clamping structure extending into the annular accommodating cavity, wherein the circumferential clamping structure comprises a third clamping claw (11) and a fourth clamping claw (12) matched with each other, the third clamping claw (11) is used for abutting against the third clamping surface (5) of the clamping part (2) of the whole turbine outer ring, and the fourth clamping claw (12) is used for abutting against the fourth clamping surface (6) of the clamping part (2) of the whole turbine outer ring; An axial limiting ring (13) is arranged between the outer casing (8) and the inner casing (9), and the axial limiting ring (13) is provided with a first clamping claw (14) extending into the annular accommodating cavity and having elasticity, the first clamping claw (14) is used for abutting against the first clamping surface (3) of the clamping part (2) of the whole turbine outer ring; the outer casing (8) is provided with a second clamping claw (15) matched with the first clamping claw (14), and the second clamping claw (15) is used for abutting against the second clamping surface (4) of the clamping part (2) of the whole turbine outer ring; After the whole turbine outer ring is mounted, a cooling channel (16) for cooling gas flow is formed between the inner casing (9) and the outer side wall of the whole turbine outer ring, the outer casing (8) is provided with an air inlet for the cooling gas, and the inner casing (9) is provided with an air outlet (21) for the cooling gas, and the cooling gas enters the cooling channel (16) from the air inlet and is discharged from the air outlet (21).

2. The mounting structure of an integral turbine outer ring according to claim 1, characterized by The first clamping surface (3) and the second clamping surface (4) are perpendicular to the axial direction of the outer ring body (1).

3. The mounting structure of an integral turbine outer ring according to claim 1, characterized by The second clamping surface (4) and the third clamping surface (5) are perpendicular to the circumferential direction of the outer ring body (1).

4. The mounting structure of an integral turbine outer ring according to any one of claims 1 to 3, characterized by, The clamping part (2) comprises an annular flange arranged along the circumferential direction of the outer ring body (1), and the front and back sides of the annular flange form the first clamping surface (3) and the second clamping surface (4); A plurality of grooves (7) are arranged on the annular flange in a circumferential direction, and the left and right sides of the grooves (7) form the third clamping surface (5) and the fourth clamping surface (6).

5. The mounting structure of an integral turbine outer ring according to any one of claims 1 to 3, characterized by The clamping part (2) comprises a plurality of protrusions arranged along the circumference of the outer ring body (1), the front and back sides of the protrusions form the first clamping surface (3) and the second clamping surface (4), and the left and right sides of the protrusions form the third clamping surface (5) and the fourth clamping surface (6).

6. The mounting structure of an integral turbine outer ring according to claim 5, characterized by The third clamping jaw (11) is rigid support, the fourth clamping jaw (12) is elastic support, and the direction in which the third clamping jaw (11) abuts against the third clamping surface (5) is opposite to the stress direction of the integral turbine outer ring in use.

7. The mounting structure of an integral turbine outer ring according to claim 6, characterized by The fourth clamping jaw (12) is in arc structure or bending structure.

8. The mounting structure of an integral turbine outer ring according to claim 7, characterized by The air inlet has double layers, and a buffer cavity (17) is formed between the air inlets on both sides, the inlet of the buffer cavity (17) is a first air inlet (18), the outlet of the buffer cavity (17) is a second air inlet (19), and the air inlet cross-sectional area of the second air inlet (19) is smaller than that of the first air inlet (18).

9. The mounting structure of an integral turbine outer ring according to claim 8, characterized by The second air inlet (19) is arranged in multiple, and the total air inlet cross-sectional area of the multiple second air inlets (19) is smaller than that of the first air inlet (18).

10. The mounting structure of an integral turbine outer ring according to any one of claims 7 to 9, characterized by, The first clamping jaw (14) of the axial limiting ring (13) is in annular integral structure, and a plurality of air vents (20) for air ventilation are arranged on the first clamping jaw (14).

11. The mounting structure of an integral turbine outer ring according to any one of claims 7 to 9, characterized by The second clamping jaw (15) on the outer casing (8) is an annular baffle extending towards the center direction, and a plurality of air outlets (21) for air outlet are arranged on the annular baffle.

12. An aeroengine characterised in that, Comprising: The mounting structure of the integral turbine outer ring according to any one of claims 1-11. The mounting structure of the integral turbine outer ring according to any one of claims 1-11.

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