A guide and a double-stage high-pressure turbine structure having the guide

Abstract

The application belongs to the technical field of aero-engines, and particularly relates to a guide vane and a two-stage high-pressure turbine structure with the guide vane. The guide vane comprises a cold gas connection nozzle, a casing, a guide vane with cooling, an inter-stage sealing ring, an inner ring, a honeycomb sealing ring, a sealing ring, and an inter-stage sealing piece. The upper edge plate of the guide vane is connected to the casing in a structure with a hook matched with a pin. The cooling gas realizes the cooling function of the guide vane through the cold gas connection nozzle. The positioning structure between the lower edge of the guide vane and the inner ring is in the form of a cylindrical pin plug. The inter-stage sealing ring is arranged between the guide vane and the inner ring to meet the requirement of reducing the leakage of main stream gas. The inner ring is a closed gas collection cavity structure, and a pre-swirl nozzle hole is arranged at the lower end. The guide vane comprises a double-layer honeycomb sealing ring, wherein the inner honeycomb ring is directly welded at the bottom position of the inner ring, the double-layer honeycomb sealing ring is centered by a stopper, and is fixed on the inner ring through bolt connection.

Description

Technical Field

[0001] This application belongs to the field of aero-engine technology, specifically a guide vane and a two-stage high-pressure turbine structure with the guide vane. Background Technology

[0002] A turbine guide vane is an annular stationary blade cascade consisting of an inner ring, an outer ring, and a set of guide vanes. Its function is to convert some of the thermal energy of the airflow into kinetic energy. Although the turbine guide vane is a stationary component, its working conditions are extremely harsh. The blades are surrounded by high-temperature gas flow and are subjected to significant thermal stress during operation. Simultaneously, due to constantly changing operating conditions, it also suffers from thermal fatigue, making it prone to fatigue cracks. In its structural design, it is necessary to ensure that each component has sufficient rigidity and strength to avoid excessive axial movement, while also allowing the components to expand freely in three directions (radial, axial, and circumferential) at high temperatures.

[0003] For multi-stage turbine rotary engines, the interstage guide vane is located between two turbine stages. Due to the significant pressure drop when airflow passes through the guide vane, a reliable sealing structure must be installed between the inner ring of the guide vane and the rotor. The inner ring of the guide vane also requires an interstage sealing structure. The purpose of the sealing structure design is to reduce energy loss caused by leakage, lower engine fuel consumption, improve engine performance, and simultaneously enhance the reliability and durability of turbine components. Summary of the Invention

[0004] To address the aforementioned problems, this application provides a guide, located on a casing between the high-pressure turbine rotor's high-vortex second-stage disk and high-vortex first-stage disk, comprising:

[0005] The cold air inlet is installed in the air vent of the casing;

[0006] The guide vane has its outer radial end fixedly connected to the casing via an upper edge plate, and its inner radial end connected to the inner ring via a lower edge plate. The guide vane has cooling holes, which are connected to a cold air inlet via through holes in the upper edge plate and to through holes in the lower edge plate.

[0007] The inner ring has a gas collecting ring cavity. The inlet of the gas collecting ring cavity is a circumferentially distributed insertion hole. The lower edge plate is connected to the insertion hole through a circumferentially distributed columnar plug so that the through hole of the lower edge plate is connected to the gas collecting ring cavity. Multiple mounting bosses connecting the side walls of the two gas collecting ring cavities are provided at a radial position of the gas collecting ring cavity.

[0008] The honeycomb sealing ring includes a first honeycomb sealing ring and a second honeycomb sealing ring. The first honeycomb sealing ring is fixedly installed on the inner ring by bolt fasteners and mounting holes of the mounting boss. The second honeycomb sealing ring is welded to the mounting platform at the end of the inner ring.

[0009] Among them, the inner ring has air intake holes and cooling air holes on the disk surface near the first-stage disk of the high-pressure vortex, and pre-rotating nozzle holes that provide cooling air to the front cavity of the second-stage disk of the high-pressure vortex.

[0010] Preferably, an interstage sealing ring is provided between the lower edge plate and the inner ring. The interstage sealing ring is installed between the lower edge plate and the inner ring and is fixed to the inner ring by fasteners.

[0011] Preferably, the fasteners include countersunk screws and bolts, with the countersunk screws positioning the interstage sealing ring and the bolts clamping and fixing the interstage sealing ring via clamping blocks.

[0012] Preferably, the interstage sealing ring has a radially protruding annular boss near the first-stage disk of the high-pressure vortex, and the lower edge plate has an annular groove. The interstage sealing ring is inserted into the annular groove through the annular boss to seal and fix the lower edge plate and the interstage sealing ring.

[0013] Preferably, the interstage sealing ring has a circumferential segmented structure. On the side near the first-stage disk of the high-vortex, there is an interstage sealing ring at the gap between two adjacent interstage sealing rings to seal the gap. The interstage sealing ring has a deep groove for inserting the interstage sealing ring.

[0014] Preferably, the countersunk screw is anti-rotation through a locking pin structure, the bolt is anti-rotation through a locking plate, and the lower edge plate has a rectangular groove to accommodate the bolt.

[0015] A two-stage high-pressure turbine structure with a guide, comprising a high-pressure turbine first-stage disk, a high-pressure turbine second-stage disk, and a guide mounted on the casing and axially positioned between the high-pressure turbine first-stage disk and the high-pressure turbine second-stage disk, wherein a sealing disk is installed between the high-pressure turbine first-stage disk and the high-pressure turbine second-stage disk, and a baffle is provided on the end face of the high-pressure turbine first-stage disk near the guide.

[0016] The baffle has a first sealing ring and a second sealing ring extending axially toward the guide direction, a third sealing ring extending axially toward the high vortex first-stage disk on the interstage sealing ring, and a fourth sealing ring extending axially toward the high vortex first-stage disk on the lower edge plate. The third sealing ring is inserted between the first sealing ring and the second sealing ring, and the first sealing ring is inserted between the third sealing ring and the fourth sealing ring to form a first sealing structure.

[0017] The interstage sealing ring has a fifth sealing ring extending axially toward the high vortex secondary disk, a sixth sealing ring extending axially toward the high vortex secondary disk on the lower edge plate, and a seventh sealing ring extending axially toward the guide direction on the high vortex secondary disk. The seventh sealing ring is inserted between the fifth and sixth sealing rings to form a second sealing structure.

[0018] The sealing disc has a first tooth structure and a second tooth structure. The first tooth structure and the second honeycomb sealing ring form a third sealing structure; the second tooth structure and the first honeycomb sealing ring form a fourth sealing structure.

[0019] The first sealing structure, the high vortex first-stage disk, the guide, and the third sealing structure form a first annular cavity for cooling the high vortex first-stage disk. The air intake hole and the cooling air hole introduce the cold air from the gas collecting annular cavity into the first annular cavity.

[0020] The sealing disk and the high-vortex secondary disk form a second annular cavity, which has vents facing the pre-swirl nozzle orifice;

[0021] The third sealing structure, the fourth sealing structure, the guide, and the sealing disc form the third annular cavity, and the sealing disc and the pre-rotating nozzle hole are all connected to the third annular cavity;

[0022] The advantages of this application include: enabling guide assembly and disassembly without splitting the second-stage rotor assembly in a confined space; having good interstage sealing function; having good resistance to thermal deformation; and having the function of adjusting cooling gas distribution and constructing axial force balancing chambers. Attached Figure Description

[0023] Figure 1 This is a schematic diagram of the guide structure according to a preferred embodiment of this application;

[0024] Figure 2 Cross-sectional view of the guide at the countersunk screw;

[0025] Figure 3 yes Figure 2 AA section view;

[0026] Figure 4 yes Figure 3 BB cross-sectional view;

[0027] Figure 5 Sectional view of the guide at the bolt;

[0028] Figure 6 yes Figure 5 CC section view;

[0029] Figure 7 yes Figure 4 The P-direction view;

[0030] Figure 8 This is a schematic diagram of a two-stage high-pressure turbine structure with a guide vane;

[0031] Figure 9 This is a gas flow diagram of a two-stage high-pressure turbine structure with a guide vane. Detailed Implementation

[0032] To make the technical solution and advantages of this application clearer, the technical solution of this application will be described in a clearer and more complete manner below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are only some embodiments of this application, and are only used to explain this application, not to limit this application. It should be noted that, for ease of description, only the parts related to this application are shown in the accompanying drawings. Other related parts can be referred to the general design. In the absence of conflict, the embodiments and technical features in the embodiments of this application can be combined with each other to obtain new embodiments.

[0033] Furthermore, unless otherwise defined, the technical or scientific terms used in this application description shall have the ordinary meaning understood by one of ordinary skill in the art to which this application pertains. The terms "upper," "lower," "left," "right," "center," "vertical," "horizontal," "inner," and "outer," etc., used in this application description to indicate relative direction or positional relationship are used only to indicate relative orientation or positional relationship, and do not imply that the device or component must have a specific orientation, or be constructed and operated in a specific orientation. When the absolute position of the described object changes, its relative positional relationship may also change accordingly, and therefore should not be construed as a limitation on this application. The terms "first," "second," "third," and similar terms used in this application description are used only for descriptive purposes to distinguish different components, and should not be construed as indicating or implying relative importance. The terms "a," "one," or "the," etc., used in this application description should not be construed as an absolute limitation on quantity, but should be construed as indicating the existence of at least one. The terms "including," "comprising," etc., used in this application description mean that the element or object preceding the word covers the element or object listed after the word and its equivalents, without excluding other elements or objects.

[0034] Furthermore, it should be noted that, unless otherwise explicitly specified and limited, terms such as “installation,” “connection,” and “linkage” used in the description of this application should be interpreted broadly. For example, a connection can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium; or it can be a connection within two components. Those skilled in the art can understand its specific meaning in this application according to the specific circumstances.

[0035] like Figure 1-8 As shown, a guide, located on a casing 2 between the high-pressure turbine rotor high-vortex second-stage disk 110 and high-vortex first-stage disk 100, includes:

[0036] The cold air inlet 1 is installed in the air vent of the casing 2;

[0037] The guide vane 3 has its outer radial end fixedly connected to the casing 2 via an upper edge plate, and its inner radial end connected to the inner ring 5 via a lower edge plate. The guide vane 3 has cooling holes, which are connected to a cooling air inlet 1 via through holes in the upper edge plate and to through holes in the lower edge plate. The upper edge plate is connected to the casing 2 using a hook and pin structure. Cooling air is supplied through the cooling air inlet 1 to cool the guide vane 3. The positioning structure between the lower edge of the guide vane 3 and the inner ring 5 uses a cylindrical pin insertion method.

[0038] The inner ring 5 has a gas collecting ring cavity. The inlet of the gas collecting ring cavity is a circumferentially distributed insertion hole. The lower edge plate is connected to the insertion hole through a circumferentially distributed columnar plug so that the through hole of the lower edge plate is connected to the gas collecting ring cavity. Multiple mounting bosses connecting the side walls of the two gas collecting ring cavities are provided at a radial position of the gas collecting ring cavity. The mounting bosses have mounting holes at their centers. In one embodiment, 36 split mounting boss structures are provided inside the gas collecting ring cavity to ensure the cooling air flow area in the cavity and increase its structural rigidity.

[0039] The honeycomb sealing ring 6 includes a first honeycomb sealing ring 61 and a second honeycomb sealing ring 62. The first honeycomb sealing ring 61 is fixedly installed on the inner ring 5 by bolt fasteners and mounting holes of the mounting boss. The second honeycomb sealing ring 62 is welded to the mounting platform at the end of the inner ring 5.

[0040] Among them, the inner ring 5 has an air intake hole M and a cooling air hole N on the disk surface near the first-stage disk 100 of the high-vortex, and a pre-swirl nozzle hole P that provides cooling air to the front cavity of the second-stage disk 110 of the high-vortex. The inner ring assembly 14, which is formed by combining the inner ring 5 with the honeycomb sealing ring 6, is fixed between the two-stage rotors using tooling, and the connecting fasteners of the two-stage rotors are tightened.

[0041] The interstage sealing ring 4 has a circumferential segmented structure. To prevent high-temperature deformation caused by its contact with the main channel gas, the front end structure is thickened to increase its structural rigidity. At the same time, a sealing groove is set in its circumferential direction and a sealing ring is set in its axial direction to prevent the leakage of the main channel gas caused by the circumferential gap of the interstage sealing ring 4 itself and the axial gap between it and the inner ring 5. The interstage sealing ring 4, the lower edge plate of the guide vane 3, the sealing ring 7 and the lower edge plate of the working blade form a labyrinth-like sealing structure.

[0042] The interstage sealing ring 4 is positioned on the clamping block 11 by countersunk screws 9 and tightened by bolts 12 in two ways on the inner ring 5. The countersunk screws use locking pins 10 to prevent rotation, and the bolts use locking plates 13 to prevent rotation. Its axial positioning is in the rectangular groove of the lower edge plate of the guide vane.

[0043] In some alternative embodiments, a sealing device, namely an interstage sealing ring 4, is provided between the lower edge plate and the inner ring 5, wherein the interstage sealing ring 4 is fixed to the inner ring 5 by fasteners.

[0044] In some alternative embodiments, the fasteners include countersunk screws 9 and bolts 12, the countersunk screws 9 positioning the interstage sealing rings 4, and the bolts 12 pressing and fixing the interstage sealing rings 4 by means of clamping blocks 11.

[0045] In some alternative embodiments, the interstage sealing ring 4 has a radially protruding annular boss, and the lower edge plate has an annular groove. The interstage sealing ring 4 is inserted into the annular groove through the annular boss to seal and fix the lower edge plate to the interstage sealing ring 4.

[0046] The interstage sealing ring 4 has a circumferential segmented structure. On the side near the first-stage disk 100 of the high vortex, there is an interstage sealing plate 8 at the gap between two adjacent interstage sealing rings 4 to block the gap. The interstage sealing ring 4 has a deep groove for inserting the interstage sealing plate 8.

[0047] A two-stage high-pressure turbine structure with a guide includes a high-pressure turbine first-stage disk 100, a high-pressure turbine second-stage disk 110, and a guide mounted on the casing 2 and axially positioned between the high-pressure turbine first-stage disk 100 and the high-pressure turbine second-stage disk 110. A sealing disk 120 is installed between the high-pressure turbine first-stage disk 100 and the high-pressure turbine second-stage disk 110, and a baffle 130 is provided on the end face of the high-pressure turbine first-stage disk 100 near the guide.

[0048] The baffle 130 has a first sealing ring b and a second sealing ring c extending axially toward the guide direction, the interstage sealing ring 4 has a third sealing ring a extending axially toward the high vortex first stage disk 100, and the lower edge plate has a fourth sealing ring d extending axially toward the high vortex first stage disk 100. The third sealing ring a is inserted between the first sealing ring b and the second sealing ring c, and the first sealing ring b is inserted between the third sealing ring a and the fourth sealing ring d, forming a first sealing structure.

[0049] The interstage sealing ring 4 has a fifth sealing ring e extending axially toward the high vortex secondary disk 110, a sixth sealing ring g extending axially toward the high vortex secondary disk 110 on the lower edge plate, and a seventh sealing ring f extending axially toward the guide direction on the high vortex secondary disk 110. The seventh sealing ring f is inserted between the fifth sealing ring e and the sixth sealing ring g to form a second sealing structure.

[0050] The sealing disc 120 has a first tooth structure 122 and a second tooth structure 121. The first tooth structure 122 and the first honeycomb sealing ring 61 form a third sealing structure; the second tooth structure 121 and the second honeycomb sealing ring 62 form a fourth sealing structure. The third and fourth sealing structures are used to change the air supply pressure and area of ​​the disc front cavity to achieve axial force balance.

[0051] The first sealing structure, the high vortex first-stage disk 100, the guide and the third sealing structure form a first annular cavity B for cooling the high vortex first-stage disk 100. The air inlet M and the cooling air inlet N introduce the cold air from the gas collecting annular cavity into the first annular cavity B, providing sealing air for the first annular cavity B, preventing the gas at the guide vane from entering the first annular cavity B, and at the same time reducing the working temperature of the components in the first annular cavity B.

[0052] The sealing plate 120 and the high-vortex secondary plate 110 form a second annular cavity A. The second annular cavity A has an air hole facing the pre-rotating nozzle hole P. The pre-rotating nozzle hole P is used to cool the high-vortex secondary plate 110, reduce the air temperature of the second annular cavity A, reduce the cooling air flow loss, and save the amount of cooling air used.

[0053] The third sealing structure, the fourth sealing structure, the guide, and the sealing disk 120 form the third annular cavity D. The sealing disk 120 and the pre-rotating nozzle hole P are all connected to the third annular cavity D.

[0054] like Figure 9 As shown, the cool air in the blade enters the stator cavity of the guide vane and is divided into two streams of gas according to the front and back. One stream of gas is drawn forward, one through hole M to cool the front disk assembly and establish the air pressure seal to the combustion gas, and the other through hole N to cool the front disk assembly. The stream of gas drawn backward provides cool air to the tenon part of the rear blade through the pre-rotation nozzle hole P.

[0055] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A guide, said guide being located on a casing (2) between a high-pressure turbine rotor high-vortex second-stage disk (110) and a high-vortex first-stage disk (100), characterized in that, include: The air inlet (1) is installed in the air vent of the casing (2); The guide vane (3) has its radial outer end fixedly connected to the casing (2) via the upper edge plate, and its radial inner end connected to the inner ring (5) via the lower edge plate. The guide vane (3) has a cooling hole, which is connected to the cold air inlet (1) via the through hole of the upper edge plate and to the through hole of the lower edge plate. The inner ring (5) has a gas collecting ring cavity. The inlet of the gas collecting ring cavity is a circumferentially distributed insertion hole. The lower edge plate is connected to the insertion hole through a circumferentially distributed columnar plug so that the through hole of the lower edge plate is connected to the gas collecting ring cavity. Multiple mounting bosses connecting the side walls of the two gas collecting ring cavities are provided at a radial position of the gas collecting ring cavity. The honeycomb sealing ring (6) includes a first honeycomb sealing ring (61) and a second honeycomb sealing ring (62). The first honeycomb sealing ring (61) is fixedly installed on the inner ring (5) by bolt fasteners and mounting holes of the mounting boss. The second honeycomb sealing ring (62) is welded to the mounting platform at the end of the inner ring (5). Among them, the inner ring (5) has an air intake hole (M), a cooling air hole (N) and a pre-rotating nozzle hole (P) for providing cooling air to the front cavity of the high vortex secondary disk (110) on the disk surface near the high vortex primary disk (100); the interstage sealing ring (4) has a radially protruding annular boss near the high vortex primary disk (100), the lower edge plate has an annular groove, and the interstage sealing ring (4) is inserted into the annular groove through the annular boss to seal and fix the lower edge plate and the interstage sealing ring (4); The interstage sealing ring (4) has a circumferential segmented structure. On the side near the first-stage disk (100) of the high vortex, there is an interstage sealing plate (8) at the gap between two adjacent interstage sealing rings (4) to seal the gap. The interstage sealing ring (4) has a deep groove for inserting the interstage sealing plate (8).

2. The guide as described in claim 1, characterized in that, There is an interstage sealing ring (4) between the lower edge plate and the inner ring (5). The interstage sealing ring (4) is installed between the lower edge plate and the inner ring (5) and is fixed to the inner ring (5) by fasteners.

3. The guide as described in claim 2, characterized in that, The fasteners include countersunk screws (9) and bolts (12). The countersunk screws (9) position the interstage sealing ring (4), and the bolts (12) press and fix the interstage sealing ring (4) by means of the clamping block (11).

4. The guide as described in claim 3, characterized in that, The countersunk screw (9) is prevented from rotating by a locking pin (10) structure, the bolt (12) is prevented from rotating by a locking plate (13), and the lower edge plate has a rectangular groove to accommodate the bolt (12).

5. A two-stage high-pressure turbine structure with a guide, comprising the guide as described in any one of claims 2-3, characterized in that, It includes a high-vortex first-stage disk (100), a high-vortex second-stage disk (110), and a guide mounted on the casing (2) and located axially between the high-vortex first-stage disk (100) and the high-vortex second-stage disk (110). A sealing disk (120) is installed between the high-vortex first-stage disk (100) and the high-vortex second-stage disk (110). The end face of the high-vortex first-stage disk (100) near the guide has a baffle (130). The baffle (130) has a first sealing ring (b) and a second sealing ring (c) extending axially toward the guide direction. The interstage sealing ring (4) has a third sealing ring (a) extending axially toward the high vortex first-stage disk (100). The lower edge plate has a fourth sealing ring (d) extending axially toward the high vortex first-stage disk (100). The third sealing ring (a) is inserted between the first sealing ring (b) and the second sealing ring (c). The first sealing ring (b) is inserted between the third sealing ring (a) and the fourth sealing ring (d) to form a first sealing structure. The interstage sealing ring (4) has a fifth sealing ring (e) extending axially toward the high vortex secondary disk (110), a sixth sealing ring (g) extending axially toward the high vortex secondary disk (110) on the lower edge plate, and a seventh sealing ring (f) extending axially toward the guide direction on the high vortex secondary disk (110). The seventh sealing ring (f) is inserted between the fifth sealing ring (e) and the sixth sealing ring (g) to form a second sealing structure. The sealing plate (120) has a first tooth structure (122) and a second tooth structure (121). The first tooth structure (122) and the first honeycomb sealing ring (61) form a third sealing structure; the second tooth structure (121) and the second honeycomb sealing ring (62) form a fourth sealing structure. The first sealing structure, the high vortex first-stage disk (100), the guide and the third sealing structure form a first annular cavity (B) for cooling the high vortex first-stage disk (100), and the air intake hole (M) and the cooling air hole (N) introduce the cold air from the gas collecting annular cavity into the first annular cavity (B). The sealing disk (120) and the high-vortex secondary disk (110) form a second annular cavity (A), which has vents facing the pre-swirl nozzle orifice (P); The third sealing structure, the fourth sealing structure, the guide and the sealing disc (120) form the third annular cavity (D), and the sealing disc (120) and the pre-rotating nozzle hole (P) are connected to the third annular cavity (D).

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