Interface constraint design method for variable cycle engine core based on conventional compressor

Abstract

The application belongs to the technical field of variable cycle core engine design, and particularly relates to a variable cycle compressor core engine interface constraint design method based on a conventional compressor, which is designed on the basis of a conventional cycle core engine configuration, selects a constraint interface, fixes typical sizes on the constraint interface, divides the core engine configuration into multiple structural modules according to the constraint interface, modularizes the core engine structure, and then obtains a variable cycle core engine by replacing and upgrading the structural modules under the constraint of the typical sizes of the constraint interface, that is, semi-constrained by the typical sizes of the constraint interface, inherits the main configuration of the conventional cycle core engine, and obtains the variable cycle core engine, so that rapid iterative design of the variable cycle core engine can be realized, in addition, the coordinates of the inner and outer flow passage interfaces in the extension range of the semi-constraint interface are fixed values, so as to ensure the smooth transition of the combination between the structural modules and the performance of the obtained variable cycle core engine.

Description

Technical Field

[0001] This application belongs to the field of variable cycle core machine design technology, specifically relating to a method for interface constraint design of a variable cycle compressor core machine based on a conventional compressor. Background Technology

[0002] The core engine is the core component of an aero engine, mainly including a high-pressure compressor, combustion chamber, and high-pressure turbine. Different series and models of aero engines can be constructed by adding low-pressure fans, low-pressure turbines, and other structures to the core engine to meet the needs of different aircraft.

[0003] A variable cycle core engine adds a front fan in front of the high-pressure compressor of a conventional cycle core engine, and an outer bypass vent valve between the front fan and the high-pressure compressor, which is the addition of a core drive fan CDFS. This is used to adjust the airflow between the inner and outer bypasses. An aero engine with a variable cycle core engine, i.e. a variable cycle aero engine, can, with proper control, have the high thrust-to-weight ratio characteristics of a turbojet engine or a small bypass turbofan engine in supersonic flight, while having low noise and low fuel consumption characteristics in subsonic flight conditions.

[0004] Currently, the classic research route for variable cycle core engines is to first conduct aerodynamic design of high-pressure compressor components → structural design of high-pressure compressor components → testing of high-pressure compressor components to form a variable cycle high-pressure compressor mechanism. Then, aerodynamic design of the core engine → structural design of the core engine → testing of the core engine are carried out. After iteration, a variable cycle core engine is obtained. This technical solution has a long cycle, high cost, and high technical risk, making it difficult to form a final product.

[0005] This application is made in view of the aforementioned technical deficiencies.

[0006] It should be noted that the above background information is only used to assist in understanding the inventive concept and technical solution of this invention, and it does not necessarily belong to the prior art of this patent application. In the absence of clear evidence that the above information was disclosed on the filing date of this application, the above background information should not be used to evaluate the novelty and inventiveness of this application. Summary of the Invention

[0007] The purpose of this application is to provide a design method for interface constraints of the core of a variable cycle compressor based on a conventional compressor, so as to overcome or mitigate at least one of the known technical defects.

[0008] The technical solution of this application is:

[0009] A method for interface constraint design of a variable cycle compressor core based on a conventional compressor, comprising:

[0010] In the conventional cycle core structure, the following constraint interfaces are selected: L1, high-pressure compressor and intermediate casing mounting interface; L2, high-pressure compressor front / rear casing mounting interface; L3, high-pressure compressor and combustion chamber outer end mounting interface; L4, high-pressure compressor and combustion chamber inner end mounting interface; L5, combustion chamber and high-pressure turbine mounting interface; L6, high-pressure turbine and low-pressure turbine mounting interface; SR1, front journal and high-pressure compressor rotor mounting interface; SR2, high-pressure compressor stage 1 and 2 rotor mounting interface; SR3, high-pressure compressor stage 2 and 3 rotor mounting interface; SR4, high-pressure compressor rotor and grate plate mounting interface; SR5, grate plate and high-pressure shaft mounting interface; and SR6, high-pressure shaft and turbine rotor mounting interface.

[0011] Typical dimensions on fixed constraint interfaces include: bolt hole height K1 on interface L1, stop height H1 on interface L1, bolt hole height K2 on interface L2, stop height H2 on interface L2, bolt hole height K3 on interface L3, stop height H3 on interface L3, bolt hole height K4 on interface L4, stop height H4 on interface L4, bolt hole height K5 on interface L5, stop height H5 on interface L5, bolt hole height K6 on interface L6, stop height H6 on interface L6; bolt hole height SK1 on interface SR1, stop height SH1 on interface SR1, bolt hole height SK2 on interfaces SR2 and SR3, stop height SH2 on interface SR2, stop height SH3 on interface SR3, bolt hole height SK4 on interfaces SR4 and SR5, stop height SH4 on interfaces SR4 and SR5, bolt hole height SK6 on interface SR6, stop height SH6 on interface SR6.

[0012] The core structure is divided into multiple structural modules based on the constraint interface;

[0013] Under the constraint of typical interface dimensions, corresponding structural modules for front-mounted fan and external bypass vent valve are designed to replace the corresponding structural modules on the conventional circulating core mechanism, and each structural module is upgraded to obtain a variable circulation core machine.

[0014] According to at least one embodiment of this application, the described interface constraint design method for a variable cycle compressor core based on a conventional compressor is characterized in that...

[0015] Within the constraint extension range of the semi-constrained interface, the coordinates of the inner and outer flow channel interfaces are fixed values.

[0016] According to at least one embodiment of this application, the described interface constraint design method for a variable cycle compressor core based on a conventional compressor is characterized in that...

[0017] The semi-constrained interface constraint extension range is ±30mm.

[0018] This application has at least the following beneficial technical effects:

[0019] This paper presents a method for interface constraint design of a variable cycle compressor core based on a conventional compressor. The design is based on the conventional cycle core structure configuration. A constraint interface is selected, and typical dimensions on the constraint interface are fixed. The core structure is divided into multiple structural modules according to the constraint interface, thus modularizing the core structure. Then, under the constraint of the typical dimensions of the constraint interface, the variable cycle core is obtained by replacing and upgrading the structural modules. In other words, the typical dimensions of the constraint interface are used for semi-constraint, inheriting the main configuration of the conventional cycle core to obtain the variable cycle core. This enables rapid iterative design of the variable cycle core. Furthermore, within the constraint extension range of the semi-constrained interface, the coordinates of the inner and outer flow channel interfaces are fixed values ​​to ensure a smooth transition between structural modules and guarantee the performance of the resulting variable cycle core. Attached Figure Description

[0020] Figure 1 This is a schematic diagram of typical dimensions of the stator constraint interface of a conventional cyclic core machine provided in the embodiments of this application;

[0021] Figure 2 This is a schematic diagram of typical dimensions of the stator constraint interface of the variable cycle core machine provided in the embodiments of this application;

[0022] Figure 3 This is a schematic diagram of typical dimensions of the rotor constraint interface of a conventional circulating core machine provided in an embodiment of this application;

[0023] Figure 4 This is a schematic diagram of typical dimensions of the rotor constraint interface of the variable cycle core machine provided in the embodiments of this application;

[0024] Figure 5 This is a schematic diagram of a conventional circulating compressor structure module provided in an embodiment of this application;

[0025] Figure 6 This is a schematic diagram of the variable cycle compressor structure module provided in the embodiments of this application;

[0026] Figure 7 This is a schematic diagram illustrating how the upgrade of the compressor components drives the upgrade of the core engine, as provided in an embodiment of this application.

[0027] Figure 8 This is a schematic diagram of a variable cycle engine formed by the combination of modules provided in the embodiments of this application;

[0028] Figure 9 This is a schematic diagram of the variable cycle engine rotor functional module provided in the embodiments of this application.

[0029] To better illustrate this embodiment, some parts in the accompanying drawings may be omitted, enlarged, or reduced, and do not represent the actual size of the product. Furthermore, the accompanying drawings are for illustrative purposes only and should not be construed as limiting this patent. Detailed Implementation

[0030] 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.

[0031] 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.

[0032] 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.

[0033] The following is in conjunction with the appendix Figures 1 to 9This application provides a more detailed description of the interface constraint design method for the core of a variable cycle compressor based on a conventional compressor.

[0034] The core machine structure is modularized, allowing each module to be independently designed or upgraded, provided that interface consistency between modules is maintained. This semi-constrained design, with typical interface dimensions as constraints, is described in [reference needed]. Figure 1-4 The conditions are as follows:

[0035] L1 is the installation interface between the high-pressure compressor and the intermediate casing; L2 is the installation interface between the front and rear casings of the high-pressure compressor; L3 is the installation interface between the high-pressure compressor and the outer end of the combustion chamber; L4 is the installation interface between the high-pressure compressor and the inner end of the combustion chamber; L5 is the installation interface between the combustion chamber and the high-pressure turbine; L6 is the installation interface between the high-pressure turbine and the low-pressure turbine.

[0036] SR1 is the mounting interface between the front journal and the high-pressure compressor rotor; SR2 is the mounting interface between the first and second stage rotors of the high-pressure compressor; SR3 is the mounting interface between the second and third stage rotors of the high-pressure compressor; SR4 is the mounting interface between the high-pressure compressor rotor and the grate plate; SR5 is the mounting interface between the grate plate and the high-pressure shaft; SR6 is the mounting interface between the high-pressure shaft and the turbine rotor.

[0037] F1 is the CDFS fan inlet; F2 is the CDFS fan outlet; F4 is the high-pressure compressor outlet and combustion chamber inlet; F5 is the combustion chamber outlet and turbine inlet.

[0038] R1-R6 are the rotor blades of the 1st to 6th stage high-pressure compressor; SW1 is the outlet stator, which is the conversion module between the high-pressure compressor outlet and the combustion chamber inlet; T1 is the rotor blade of the high-pressure turbine.

[0039] Guarantee arbitrary combinations between structural modules:

[0040] K1 is the bolt hole height of interface L1, and H1 is the stop height of interface L1, both are fixed values.

[0041] K2 is the bolt hole height of interface L2, and H2 is the stop height of interface L2, both are fixed values.

[0042] K3 is the bolt hole height of interface L3, and H3 is the stop height of interface L3, both are fixed values.

[0043] K4 is the bolt hole height of the L4 interface, and H4 is the stop height of the L4 interface, both are fixed values.

[0044] K5 is the bolt hole height of interface L5, and H5 is the stop height of interface L5, both are fixed values.

[0045] K6 is the bolt hole height of interface L6, and H6 is the stop height of interface L6, both are fixed values.

[0046] SK1 is the bolt hole height of the SR1 interface, and SH1 is the stop height of the SR1 interface. The value can be either a dynamic or fixed value, just enough to ensure that the structural modules can be assembled.

[0047] SK2 is the bolt hole height at the interface between SR2 and SR3, and SH2 is the stop height at the interface of SR2, both are fixed values.

[0048] SH3 is the stop height of the SR3 interface, a fixed value;

[0049] SK4 is the bolt hole height at the interface between SR4 and SR5, and SH4 is the stop height at the interface between SR4 and SR5, both are fixed values.

[0050] SK6 is the bolt hole height of the SR6 interface, and SH6 is the stop height of the SR6 interface; both are fixed values.

[0051] XL2 is the abscissa of L2 plane, XL3 is the abscissa of L3 plane, XL4 is the abscissa of L4 plane, XL5 is the abscissa of L5 plane, (Xi, Y1, i) is the core machine internal flow channel coordinate i=1,2,3……; (Xj, Y2, j) is the core machine external flow channel coordinate j=1,2,3…….

[0052] Xi+1 - Xi = 1~10 mm; Xj+1 - Xj = 1~10 mm; within ±30 mm of the interfaces of L2, L3, L4, L5, and L6, (Xi, Y1, i) and (Xj, Y2, j) are fixed values.

[0053] XL2 = Length of the front casing of the high-pressure compressor; XL3 = Length of the casing of the high-pressure compressor; XL3 - XL2 = Length of the rear casing of the high-pressure compressor; XL4 - XL3 = Length of the conversion module; XL5 - XL4 = Length of the combustion chamber; XL6 - XL5 = Length of the turbine casing.

[0054] XSR2 - XSR1 = First stage rotor + front journal length; XSR4 - XSR1 = High pressure compressor rotor axial length; XSR6 - XSR5 = High pressure shaft length.

[0055] The core engine module is hierarchically divided into: structural modules, component functional modules, and core engine functional modules. Structural modules combine to form component functional modules, and component functional modules combine to form core engine functional modules. If the "core engine" is defined as a first-level functional module, the high-pressure compressor, combustion chamber, and high-pressure turbine will be defined as second-level functional modules. Functional modules can individually perform specific functions, and functional modules are composed of structural modules.

[0056] Taking the functional modules of the high-pressure compressor as an example, we can break them down and identify the structural modules. The functional modules of the high-pressure compressor can be divided into major structural modules such as the high-pressure compressor rotor, the front casing, the rear casing, and the front journal. See [link / reference]. Figure 5-6 ,in:

[0057] 11 is a conventional cycle high-pressure compressor component module; 12 is a combustion chamber component module; 13 is a high-pressure turbine component module; 31 is a variable cycle high-pressure compressor component module;

[0058] P01 is the front casing structure module; P02 is the rear casing structure module; P101 is the front casing structure module with bypass bleed air.

[0059] CM2 is a standard front axle journal structure module; N2 is a variable cycle dedicated front axle journal structure module.

[0060] CM3 is a single-stage rotor structure module; N3 is a CDFS fan + high-voltage single-stage rotor structure module.

[0061] CM4 is a two-stage rotor structure module;

[0062] CM5 is a 3- to 6-stage rotor structure module;

[0063] SW1 is the high-pressure compressor / combustion chamber component switching module, corresponding to the function exchange unit at the component interface.

[0064] Under semi-constraint conditions, the high-pressure compressor, combustion chamber, and high-pressure turbine can be upgraded by individual component functional modules or structural modules. After the module upgrade is completed, it can be directly installed on the core engine, thereby promoting the upgrade of the entire core engine.

[0065] In a specific embodiment, under the semi-constrained design criteria, to meet the requirements of weight reduction and rotor length shortening for aero-engines, the high-pressure compressor can be shortened to a 3-5 stage high-pressure compressor component functional module without affecting the performance of the aero-engine. Interfaces L1, L3, SR1, and SR5 satisfy the semi-constrained design criteria, such as... Figure 7 As shown, where,

[0066] 11. Upgrade the functional modules of the first 6 stages of high-pressure compressor components;

[0067] 21 represents the functional modules of the upgraded 3-5 stage high-pressure compressor components.

[0068] The L1 interface of the conventional cycle core engine is replaced, and the L2 interface meets the semi-constrained design requirements. The coordinates (Xi, Y1, i) and (Xj, Y2, j) after the F3 surface are consistent with the original high-pressure compressor flow channel coordinates. The K1-1-1 module is replaced with the K2 module, forming the variable cycle high-pressure compressor component module, such as... Figure 8As shown, where:

[0069] K1 is a conventional cycle engine;

[0070] K1-1 is the core machine module formed by 11+12+13;

[0071] K1-1-1 is a high-pressure compressor pre-unit consisting of P01 + CM3;

[0072] K1-1-2 is the remaining core unit consisting of the split unit of P02+ SW1+ CM4+CM5 high-pressure compressor and units 12 and 13;

[0073] K2 is a CDFS unit composed of P101 + N3;

[0074] K3 is the intermediate casing intake section containing N2;

[0075] K4 is the exhaust section;

[0076] K12 is a variable-cycle core machine module consisting of K2+K1-1-2;

[0077] K5 is a test piece for a variable-cycle core machine consisting of K3 + K4 + K12;

[0078] The K6 is a variable cycle engine with the K12 as its core component.

[0079] With the combustion chamber and turbine modules remaining unchanged, a variable cycle CDFS unit module is added to form a variable cycle core engine module;

[0080] The variable cycle core engine module is equipped with a K3 intermediate intake casing module and a K4 exhaust section module in front of and behind it, forming the variable cycle core engine test piece K5, which is used for performance testing and performance determination of the variable cycle core engine.

[0081] After the variable cycle core engine prototype K5 passed test runs, it was fitted with front and rear fans and low-pressure turbine modules to form the variable cycle engine K6. Figure 8 As shown.

[0082] The venting mechanism of CDFS can adopt the ducted ejector configuration of the variable cycle engine in CN109162829B, and the overall configuration of the variable cycle engine can adopt the configuration design in patent CN1975130B.

[0083] The conventional cycle engine rotor consists of a first-stage rotor structure module CM3, a front journal structure module CM2, a 3-6 stage rotor structure module CM5, a high-pressure shaft structure module CM6, a high-pressure turbine rotor structure module CM7, a front support structure module CM1, and a rear support CM8. The variable cycle engine rotor consists of a CDFS fan + a high-pressure first-stage rotor module N3 (dedicated module), a front journal dedicated module N2, a 3-6 stage rotor structure module CM5, a high-pressure shaft structure module CM6, a high-pressure turbine rotor structure module CM7, a front support structure module N1, and a rear support CM8.

[0084] Using the front mounting edge of the secondary rotor as the rotor module installation interface, the CM3+CM2 module is replaced by the N3+N2 module, and the front point position is axially moved forward, forming the variable cycle core machine rotor. The main structure of the rotor inherits the main structure of the secondary rear rotor, such as... Figure 9 As shown.

[0085] The interface constraint design method for a variable cycle compressor core based on a conventional compressor disclosed in the above embodiments can be understood by those skilled in the art as follows: a variable cycle core can be formed by simply adding a CDFS module to the front end of the high-pressure compressor on the basis of a conventional cycle engine core. The functional modules and structural modules of each component can be upgraded individually to improve the performance of the core and the whole machine. This method enables rapid design, production and testing of the variable cycle core, which can greatly shorten the R&D cycle and reduce R&D costs.

[0086] The various embodiments in the specification are described in a progressive manner, with each embodiment focusing on the differences from other embodiments. The same or similar parts between the various embodiments can be referred to each other.

[0087] The technical solution of this application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of this application is obviously not limited to these specific embodiments. Without departing from the principles of this application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will all fall within the scope of protection of this application.

Claims

1. A method for interface constraint design of a core unit of a variable cycle compressor based on a conventional compressor, characterized in that, include: In the conventional cycle core structure, the following constraint interfaces are selected: L1, high-pressure compressor and intermediate casing mounting interface; L2, high-pressure compressor front / rear casing mounting interface; L3, high-pressure compressor and combustion chamber outer end mounting interface; L4, high-pressure compressor and combustion chamber inner end mounting interface; L5, combustion chamber and high-pressure turbine mounting interface; L6, high-pressure turbine and low-pressure turbine mounting interface; SR1, front journal and high-pressure compressor rotor mounting interface; SR2, high-pressure compressor stage 1 and 2 rotor mounting interface; SR3, high-pressure compressor stage 2 and 3 rotor mounting interface; SR4, high-pressure compressor rotor and grate plate mounting interface; SR5, grate plate and high-pressure shaft mounting interface; and SR6, high-pressure shaft and turbine rotor mounting interface. Typical dimensions on fixed constraint interfaces include: bolt hole height K1 on interface L1, stop height H1 on interface L1, bolt hole height K2 on interface L2, stop height H2 on interface L2, bolt hole height K3 on interface L3, stop height H3 on interface L3, bolt hole height K4 on interface L4, stop height H4 on interface L4, bolt hole height K5 on interface L5, stop height H5 on interface L5, bolt hole height K6 on interface L6, stop height H6 on interface L6; bolt hole height SK1 on interface SR1, stop height SH1 on interface SR1, bolt hole height SK2 on interfaces SR2 and SR3, stop height SH2 on interface SR2, stop height SH3 on interface SR3, bolt hole height SK4 on interfaces SR4 and SR5, stop height SH4 on interfaces SR4 and SR5, bolt hole height SK6 on interface SR6, stop height SH6 on interface SR6. The core structure is divided into multiple structural modules based on the constraint interface; Under the constraint of typical interface dimensions, corresponding structural modules for front-mounted fan and external bypass vent valve are designed to replace the corresponding structural modules on the conventional circulating core mechanism, and each structural module is upgraded to obtain a variable circulation core machine.

2. The interface constraint design method for the core machine of a variable cycle compressor based on a conventional compressor according to claim 1, characterized in that, Within the constraint extension range of the semi-constrained interface, the coordinates of the inner and outer flow channel interfaces are fixed values.

3. The interface constraint design method for the core machine of a variable cycle compressor based on a conventional compressor according to claim 2, characterized in that, The semi-constrained interface constraint extension range is ±30mm.

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