Gas compressor casing, gas compressor and application of gas compressor

Abstract

The invention belongs to the technical field of aero-engines, and particularly relates to a gas compressor casing, a gas compressor and application of the gas compressor casing. The invention provides a gas compressor casing which comprises a casing body and a gap control structure, and the gap control structure is arranged in an annular groove of the gas compressor casing. The gap control structure comprises a blade ring, a first gasket and a second gasket, the blade ring is arranged in the annular groove, the first gasket and the second gasket are arranged on the inner side and the outer side of the blade respectively, the first gasket and the blade ring form an annular cavity in the annular groove, and the blade ring can move in the annular cavity. The invention further provides a gas compressor comprising the gas compressor casing. The invention further provides application of the gas compressor casing or the gas compressor in an aero-engine. According to the blade tip clearance adjusting device, high-pressure gas enters the annular cavity, the blade ring extrudes the second gasket after being subjected to the pressure of the high-pressure gas, the blade ring moves towards the direction of the second gasket, the lifting of the annular cavity is changed, and adjustment of the blade tip clearance is achieved.

Description

Technical Field

[0001] The present application belongs to the technical field of aero-engines, and in particular relates to a compressor casing, a compressor and applications thereof. Background Art

[0002] The compression system is one of the important components of an aircraft engine, and its working efficiency has a great impact on the performance level of the aircraft engine. Among them, the tip clearance design is one of the important factors affecting the working efficiency of the compression system.

[0003] The main factors affecting the tip clearance include: dimensional tolerance of manufacturing, position accuracy, deformation of parts under thermal expansion or load, deformation of the load-bearing system and shaft system under load conditions, part warping caused by uneven heating and loading, changes in part position caused by part matching clearance, and the position of adjustable parts. In the prior art, the tip clearance of the compression system is mainly fixed, and the tip clearance of some engine compression systems adopts passive clearance control, which cannot automatically adjust the tip clearance according to the working state of the engine, further resulting in low working efficiency of the compression system.

[0004] Therefore, developing a compressor casing, a compressor and applications thereof to solve the technical defect in the prior art that the engine tip clearance cannot be actively adjusted according to the working state has become an urgent problem to be solved by technical personnel in this field. Summary of the invention

[0005] Based on this, it is necessary to provide a compressor casing, a compressor and their applications to address the technical defect in the existing technology that the engine tip clearance cannot be actively adjusted according to the working status.

[0006] The present application provides a compressor casing, the compressor casing comprising: a casing body and a gap control structure, the gap control structure being arranged in an annular groove of the compressor casing;

[0007] The gap control structure includes: a blade ring, a first gasket and a second gasket. The blade ring is arranged in the annular groove. The first gasket and the second gasket are respectively arranged on the inner and outer sides of the blade. The first gasket and the blade ring form an annular cavity in the annular groove. The blade ring can move in the annular cavity.

[0008] In one of the embodiments, the gap control structure also includes: an air intake joint, the blade ring is provided with an air vent connected to the pressure gas in the compressor, the air intake joint is externally connected to the pressure gas in the compressor, and the pressure gas in the compressor enters the annular cavity through the air vent.

[0009] In one embodiment, the first gasket is an elastic structure, and the second gasket is an elastic structure.

[0010] In one embodiment, the number of the leaf rings is greater than two, and the leaf rings are fan-shaped structures.

[0011] In one embodiment, the blade ring includes: a plurality of stator blades and a blade casing, and the stator blades are installed in the blade casing.

[0012] In one of the embodiments, the gap control structure further includes: a sealing sheet, wherein the sealing sheet is arranged between adjacent blade rings.

[0013] In one embodiment, the maximum deformation of the second gasket is the maximum adjustment gap.

[0014] The present application also provides a compressor, which includes the compressor casing described in any one of the above.

[0015] The present application also provides a compressor casing comprising any one of the above or an application of the above compressor in an aircraft engine.

[0016] In summary, the present application provides a compressor casing, including: a casing body and a gap control structure, wherein the gap control structure is arranged in an annular groove of the compressor casing; the gap control structure includes: a blade ring, a first gasket and a second gasket, wherein the blade ring is arranged in the annular groove, wherein the first gasket and the second gasket are arranged on the inner and outer sides of the blade respectively, wherein the first gasket and the blade ring form an annular cavity in the annular groove, wherein the blade ring can move in the annular cavity. The present application also provides a compressor including the compressor casing, and the present application also provides an application of the compressor casing or the compressor in an aircraft engine. In the technical solution provided by the present application, high-pressure gas enters the annular cavity of the first gasket, and the blade ring squeezes the second gasket after being subjected to the pressure of the high-pressure gas, and the blade ring moves in the direction of the second gasket, and the annular cavity changes, thereby realizing the adjustment of the tip clearance. The compressor casing, the compressor and the application provided by the present application solve the technical defect in the prior art that the tip clearance of the engine cannot be actively adjusted according to the working state. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on the provided drawings without paying any creative work.

[0018] Figure 1In the technical solution provided in the embodiment of the present application, a schematic diagram of the structure of a compressor casing;

[0019] Figure 2 A schematic structural diagram of a gap control structure in a compressor casing provided in an embodiment of the present application;

[0020] Figure 3 A partially enlarged schematic diagram of a gap control structure in a compressor casing provided in an embodiment of the present application;

[0021] Figure 4 Another partially enlarged schematic diagram of a gap control structure in a compressor casing provided in an embodiment of the present application;

[0022] Among them, there are a gap control structure 1, a compressor casing 2, a blade ring 3, a second gasket 4, a first gasket 5, an air inlet joint 6, an annular groove 7, an annular cavity 8, an air vent 9, an internal air source 10, an external air source 11, a stator blade cascade 12, a blade cascade housing 13, a sealing sheet 14, a rotor 15, a first radial gap 16, a second radial gap 17 and an annular cavity 18. DETAILED DESCRIPTION

[0023] The embodiments of the present application provide a compressor casing, a compressor and applications thereof, which are used to solve the technical defect in the prior art that the engine tip clearance cannot be actively adjusted according to the working state.

[0024] In order to make the above-mentioned purposes, features and advantages of the present application more obvious and easy to understand, the specific implementation methods of the present application are described in detail below in conjunction with the accompanying drawings. In the following description, many specific details are set forth to facilitate a full understanding of the present application. However, the present application can be implemented in many other ways different from those described herein, and those skilled in the art can make similar improvements without violating the connotation of the present application, so the present application is not limited by the specific embodiments disclosed below.

[0025] In the description of the present application, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise", "axial", "radial", "circumferential" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present application.

[0026] In addition, the terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" and "second" may explicitly or implicitly include at least one of the features. In the description of this application, the meaning of "plurality" is at least two, such as two, three, etc., unless otherwise clearly and specifically defined.

[0027] In this application, unless otherwise clearly specified and limited, the terms "installed", "connected", "connected", "fixed" and the like should be understood in a broad sense, for example, it 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, it can be the internal connection of two elements or the interaction relationship between two elements, unless otherwise clearly defined. For ordinary technicians in this field, the specific meanings of the above terms in this application can be understood according to specific circumstances.

[0028] In the present application, unless otherwise clearly specified and limited, a first feature being “above” or “below” a second feature may mean that the first and second features are in direct contact, or the first and second features are in indirect contact through an intermediate medium. Moreover, a first feature being “above”, “above”, and “above” a second feature may mean that the first feature is directly above or obliquely above the second feature, or simply means that the first feature is higher in level than the second feature. A first feature being “below”, “below”, and “below” a second feature may mean that the first feature is directly below or obliquely below the second feature, or simply means that the first feature is lower in level than the second feature.

[0029] It should be noted that when an element is referred to as being "fixed to" or "disposed on" another element, it may be directly on the other element or there may be a central element. When an element is considered to be "connected to" another element, it may be directly connected to the other element or there may be a central element at the same time. The terms "vertical", "horizontal", "upper", "lower", "left", "right" and similar expressions used herein are for illustrative purposes only and are not intended to be the only implementation method.

[0030] See also Figures 1 to 4The embodiment of the present application provides a compressor casing 2, comprising: a casing body and a clearance control structure 1, the clearance control structure 1 is arranged in the annular groove 7 of the compressor casing 2; the clearance control structure 1 comprises: a blade ring 3, a first gasket 5 and a second gasket 4, the blade ring 3 is arranged in the annular groove 7, the first gasket 5 and the second gasket 4 are arranged on the inner and outer sides of the blade respectively, the first gasket 5 and the blade ring 3 form an annular cavity 8 in the annular groove 7, and the blade ring 3 can move in the annular cavity 8. The embodiment of the present application provides a compressor casing 2, which solves the technical defect in the prior art that the engine blade tip clearance cannot be actively adjusted according to the working state.

[0031] In the technical solution provided in the embodiment of the present application, the principle of pressure-type active clearance control is adopted. After the external gas source 11 of the compressor casing 2 enters the internal annular cavity of the first gasket 5, the external gas source 11 pushes the blade ring 3 to move in the direction of the second gasket 4. At this time, the second gasket 4 is deformed after being compressed to produce a deformation amount Δl. Correspondingly, the blade ring 3 also moves Δl in the annular groove 7, and the volume of the annular cavity 8 between the blade ring 3 and the first gasket 5 changes, that is, a one-time position adjustment is achieved. Similarly, when the gas pressure of the external gas source 11 changes, the position of the blade ring 3 will continue to move, achieving the technical effect of actively adjusting the engine tip clearance according to the working state (intake pressure).

[0032] In the technical solution provided in the embodiment of the present application, by utilizing the change in gas pressure in the annular cavity 18 entering the first gasket 5, the second gasket 4 undergoes elastic deformation, and the gas pressure change in the annular cavity 8 entering the vent 9, the design requirement of adjusting the blade tip clearance of the compressor casing 2 in real time according to its working state is achieved, the problem of low working efficiency caused by fixed clearance is solved, and efficient and reliable operation of the compression system is achieved.

[0033] To further optimize the technical solution, in a compressor casing 2 provided in an embodiment of the present application, the gap control structure 1 also includes: an air intake connector 6, a first gasket 5 connected to the air intake connector 6, the air intake connector 6 is externally connected to an external air source 11, and the external air source 11 enters the annular cavity 8 through the air vent 9.

[0034] When the intake pressure of the external gas source 11 does not change, the gas pressure in the annular cavity 8 is opposite to the gas pressure of the internal gas source 10 of the compressor casing 2. At this time, the gas pressure transmitted to the second gasket 4 is small, and the blade ring 3 is in a balanced state and does not move.

[0035] In a further design, the first gasket 5 expands under the action of the gas pressure in the annular cavity 18 and transmits the force to the second gasket 4 through the movable blade ring 3. The second gasket 4 produces a deformation amount Δl under the action of the force, and the blade ring 3 moves Δl in the annular groove 7 of the compressor casing, that is, a position adjustment is achieved. When the gas pressure in the annular cavity 18 changes, the working position of the blade ring 3 changes with the deformation amount Δl of the second gasket 4, that is, the first radial gap 16 and the second radial gap 17 formed between the movable blade ring 3 and the rotor 15 of the compression system change accordingly, thereby realizing the active adjustment of the tip clearance of the compression system.

[0036] The leaf ring 3 is provided with a vent hole 9, and the high-pressure gas of the internal gas source 10 in the compression system enters the annular cavity 8 through the vent hole 9. The annular cavity 8 is a sealed cavity. The leaf ring 3 is acted upon by the gas pressure in the annular cavity 8 and the high-pressure gas pressure of the internal gas source 10 in the compression channel. The remaining force after the two forces are balanced is transmitted from the leaf ring 3 to the second gasket 4 or the first gasket 5.

[0037] In a further embodiment, since the gas pressure in the annular cavity 8 is in opposite directions to the high-pressure gas pressure of the gas source 10 inside the compression passage, the gas pressure transmitted to the second gasket 4 or the first gasket 5 is relatively small. At this time, the movable blade ring 3 is basically in a working follow-up balance state, and the balance position of the movable blade ring 3 in the compressor casing can be adjusted by adjusting the pressure in the annular cavity 18.

[0038] The rigidity (k5) of the first gasket 5 is equal to the rigidity (k4) of the second gasket 4 (k5=k4), which is one order of magnitude smaller than the rigidity (k3) of the mounting edge of the movable blade ring 3, so as to ensure that the movable blade ring 3 only transmits force outward without deformation under the action of the gas pressure in the annular cavity 18.

[0039] In the working state, the second gasket 4 generates a compression deformation δ1 under the action of the gas pressure in the annular cavity 18, and the first gasket 5 generates a compression deformation δ2 under the action of the gas pressure in the annular cavity 18, and δ1=δ2.

[0040] A further design scheme ensures that the deformation of the second gasket 4 and the first gasket 5 is linearly related to the pressure in the annular cavity 18, that is, under the working environment, the second gasket 4 and the first gasket 5 are within the linear elastic range, that is, the working position of the movable blade ring 3 and the pressure in the annular cavity 18 are unique, thereby ensuring the accuracy of the tip clearance adjustment.

[0041] In the scheme, the maximum deformation δmax of the second gasket 4 should be given according to the maximum adjustment requirement of the system. The maximum adjustment requirement is generally taken as the maximum deformation difference △1, △2 between the typical adjustment state (such as cruising state, maximum continuous state) and the minimum clearance state (such as slow speed to take-off state), and max(△1, △2) is taken, that is, δmax=max(△1, △2).

[0042] The maximum deformation δ of the second gasket 4 max It occurs when the gas pressure in the annular cavity 18 is maximum Pmax, that is, the maximum working state of the compression system, so the stiffness of the second gasket 4 and the first gasket 5 is k=Pmax / δmax.

[0043] By utilizing the stiffness k of the second gasket 4 and the first gasket 5 selected by the design, the adjustment amounts △1 and △2 under the typical states (such as state 1 and state 2) that need to be adjusted, the function relationship curve of the compression system pressure versus the axial position, and the functional relationship of k=Pmax / δ, the appropriate bleed air position is selected on the compressor and determined after completing the simulation and comprehensive analysis.

[0044] The following is an example to illustrate the specific design steps:

[0045] 1) Perform a force analysis on the blade ring 3 during operation and select the position and size of its vent hole 9;

[0046] 2) Perform gap change analysis within a working section and select typical adjustment values ​​△1 and △2 (multiple values ​​can be selected based on project adjustment requirements);

[0047] 3) Select the thickness dimension L4 of the second gasket 4 ≥ 20max (△1, △2);

[0048] 4) Select the thickness dimension L5 of the first gasket 5 ≥ 20max (△1, △2);

[0049] 5) Select the thickness dimension L3 of the installation edge of the blade ring 3, which can be convenient for processing;

[0050] 6) Select the groove width dimension L2 of the annular groove on the compressor casing; ensure that L2 = L3 + L4 + L5.

[0051] 7) Select the stiffness k=Pmax / max(△1,△2) of the second gasket 4 and the first gasket 5, where Pmax is the selected bleed air pressure under the state corresponding to max(△1,△2);

[0052] 8) Complete the drawing of the relationship curve between the compression system pressure and the axial position function;

[0053] 9) Select other typical states (such as min(△1, △2)), and use the design function relationship between k, △, and P to select the air inlet position Z that meets the pressure regulation requirements.

[0054] 10) During operation, according to the working state, select the air inlet position Z connected to the annular cavity 18 of the first gasket 5,

[0055] To achieve the adjustment of blade tip clearance in typical conditions.

[0056] In a compressor casing 2 provided in an embodiment of the present application, in order to facilitate the installation of the blade ring 3 and better match the structure of the annular groove 7, the number of the blade rings 3 is greater than two, and the blade ring 3 is a fan-shaped structure.

[0057] To further optimize the structure of the blade ring 3, in the technical solution provided in the embodiment of the present application, the blade ring 3 includes: a plurality of stator blade cascades 12 and a blade cascade housing 13, and the stator blade cascade 12 is installed in the blade cascade housing 13. At this time, a first radial gap 16 is formed between the stator blade cascade 12 and the rotor 15 of the compressor, and a second radial gap 17 is formed between the blade cascade housing 13 and the rotor 15 of the compressor, and the tip clearance is adjusted by changing the position of the blade ring 3.

[0058] To further optimize the technical solution, in the compressor casing 2 provided in the embodiment of the present application, the clearance control structure 1 further includes: a sealing sheet 14, which is arranged between adjacent blade rings 3. The sealing sheet 14 can ensure that the annular cavity 8 formed between the adjacent blade rings 3 and the first gasket 5 does not interfere with each other, further ensuring the accuracy of the blade tip clearance adjustment.

[0059] The present application also provides a compressor including a compressor casing having any of the above technical features. After the compressor casing is installed, the tip clearance can be actively adjusted according to the pressure of the incoming external airflow, and can be widely used in the field of aviation engine technology.

[0060] In summary, the present application provides a compressor casing, comprising: a casing body and a gap control structure, wherein the gap control structure is arranged in an annular groove of the compressor casing; the gap control structure comprises: a blade ring, a first gasket and a second gasket, wherein the blade ring is arranged in the annular groove, wherein the first gasket and the second gasket are arranged on the inner and outer sides of the blade respectively, wherein the first gasket and the blade ring form an annular cavity in the annular groove, wherein the blade ring can move in the annular cavity. The present application also provides a compressor including the compressor casing, and the present application also provides an application of the compressor casing or the compressor in an aircraft engine. In the technical solution provided by the present application, high-pressure gas enters the annular cavity, and the blade ring squeezes the second gasket after being subjected to the pressure of the high-pressure gas, and the blade ring moves in the direction of the second gasket, and the annular cavity changes, thereby realizing the adjustment of the tip clearance. The compressor casing, the compressor and the application provided by the present application solve the technical defect in the prior art that the tip clearance of the engine cannot be actively adjusted according to the working state.

[0061] The technical features of the above-mentioned embodiments can be combined arbitrarily. To make the description concise, not all possible combinations of the technical features in the above-mentioned embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification. At the same time, other implementation methods can be derived from the above-mentioned embodiments, so that structural and logical replacements and changes can be made without departing from the scope of this disclosure.

[0062] The above-described embodiments only express several implementation methods of the present application, and the descriptions thereof are relatively specific and detailed, but they cannot be construed as limiting the scope of the patent application. It should be pointed out that, for a person of ordinary skill in the art, several variations and improvements can be made without departing from the concept of the present application, and these all belong to the protection scope of the present application. Therefore, the protection scope of the patent application shall be subject to the attached claims.

Claims

1. A compressor casing, characterized in that: The compressor casing comprises: a casing body and a gap control structure, wherein the gap control structure is arranged in an annular groove of the compressor casing; The gap control structure includes: a blade ring, a first gasket and a second gasket. The blade ring is arranged in the annular groove. The first gasket and the second gasket are respectively arranged on the inner and outer sides of the blade. The first gasket and the blade ring form an annular cavity in the annular groove. The blade ring can move in the annular cavity.

2. The compressor casing according to claim 1, characterized in that: The gap control structure also includes: an air intake joint, the leaf ring is provided with an air vent connected to the air intake joint, the air intake joint is connected to an external air source, and the air source enters the annular cavity through the air vent.

3. The compressor casing according to claim 1 or 2, characterized in that: The first gasket is an elastic structure, and the second gasket is an elastic structure.

4. The compressor casing according to any one of claims 1 to 3, characterized in that: The number of the leaf rings is greater than two, and the leaf rings are fan-shaped structures.

5. The compressor casing according to claim 4, characterized in that: The blade ring includes: a plurality of stator blade cascades and a blade cascade casing, and the stator blade cascades are installed in the blade cascade casing.

6. The compressor casing according to claim 4 or 5, characterized in that: The gap control structure further includes: a sealing sheet, and the sealing sheet is arranged between adjacent blade rings.

7. The compressor casing according to claim 3, characterized in that: The maximum deformation amount of the second gasket is the maximum adjustment amount of the blade tip clearance, and the maximum deformation amount of the first gasket is the maximum deformation amount of the second gasket.

8. A compressor, characterized in that: The compressor comprises the compressor casing according to any one of claims 1 to 7.

9. Use of the compressor casing according to any one of claims 1 to 7 or the compressor according to claim 8 in an aircraft engine.

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