CN110132556B - Modular turbine test piece and test method thereof - Google Patents
Modular turbine test piece and test method thereof Download PDFInfo
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- CN110132556B CN110132556B CN201910357966.3A CN201910357966A CN110132556B CN 110132556 B CN110132556 B CN 110132556B CN 201910357966 A CN201910357966 A CN 201910357966A CN 110132556 B CN110132556 B CN 110132556B
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Abstract
The invention discloses a modularized turbine test piece and a test method thereof, wherein the modularized turbine test piece comprises the following components: the test device comprises an air inlet system, an exhaust system and a rotor system, wherein a test component which is coaxially arranged and used for realizing a turbine test piece simulation test under different flow channel parameters is arranged between the air inlet system and the exhaust system; the rotor system comprises an impeller disc and a guider, wherein the impeller disc is used for adjusting the rotor system to rotate and do work according to different flow channel parameters, and the guider is used for being matched with the impeller disc to form a working section of the modularized turbine test piece. The modularized turbine test piece disclosed by the invention realizes a turbine test piece simulation test under different flow channel parameters, only matched test components, impeller discs and guides need to be designed based on the flow channel parameters, and then the test components, the impeller discs and the guides are assembled and combined, namely an air inlet system, an exhaust system and a rotor system except the impeller discs are used as common modules, and the test components, the impeller discs and the guides are used as replacement modules, so that the turbine test piece simulation test under different flow channel parameters is realized.
Description
Technical Field
The invention relates to the field of turbine test pieces, in particular to a modularized turbine test piece. In addition, the invention also relates to a test method comprising the modular turbine test piece.
Background
Turbine test pieces are essential to the operation of aircraft engine design. The turbine test piece is based on the similar principle with the real turbine, namely: geometric similarity, motion similarity and power similarity, determining simulation parameters of a test piece, simulating and obtaining the working condition of the turbine under the real working condition by measuring parameters such as power, rotating speed, flow, total characteristics of pneumatic parameters, an outlet flow field map and the like, and further verifying and evaluating the design of the turbine of an engine of a certain model, researching the performance of the turbine and the flow field, thereby providing an important basis for the development of the turbine of the aero-engine.
At present, the traditional turbine test piece design method adopted by each unit in the domestic aviation field is designed independently by referring to the real engine structural layout and other previous test piece layout structures according to the turbine test piece simulation parameters obtained after conversion, including pneumatic layout, rotating speed, flow, temperature, pressure, expansion ratio and the like. Because each parameter of each turbine test piece is different according to the model of real engine, and the structure of each turbine test piece is also different, when carrying out a test, all need complete processing a whole set of parts. The design and processing workload and the cost of the turbine test piece are high, and the error accumulation of newly processed parts brings uncertainty to each set of test piece, so that the stability of a test result is influenced. As shown in fig. 1, each turbine test piece is similar to a small engine, and an air inlet system, an exhaust system, a rotor system, an oil system, a sealing system, a testing system and the like are all complete, and have a complex structure and a large number of parts forming the test piece.
Disclosure of Invention
The invention provides a modularized turbine test piece and a test method thereof, and aims to solve the technical problems that an air inlet system, an exhaust system, a rotor system, a lubricating oil system and the like need to be redesigned and processed, the processing cost is high, and the number of processed parts is large when the flow channel parameters of the turbine test piece in the prior art are changed.
The technical scheme adopted by the invention is as follows:
a modular turbine test piece, comprising: the turbine test piece simulation test device comprises an air inlet system, an exhaust system and a rotor system, wherein a test component which is coaxial with the air inlet system and the exhaust system and is used for realizing a turbine test piece simulation test under different runner parameters is arranged between the air inlet system and the exhaust system; the rotor system comprises an impeller disc for adjusting the rotor system to rotate and apply work according to different flow channel parameters; a guide for interacting with the impeller disk and forming a working section of the modular turbine test piece.
Furthermore, the air inlet system and the test assembly and the exhaust system and the test assembly are detachably connected for realizing the convenience of replacing the test assembly under different flow channel parameters; the detachable connection adopts one of ladder splicing opening connection, concave-convex connection or splicing.
Furthermore, the testing component comprises a front testing mechanism, a working section testing mechanism and a rear testing mechanism which are sequentially arranged; the air inlet system comprises an air inlet inner casing and an air inlet outer casing, and the front testing mechanism comprises a front testing inner casing and a front testing outer casing; the air inlet inner casing and the front test inner casing are assembled and combined, and the air inlet outer casing and the front test outer casing are assembled and combined; the exhaust system comprises an exhaust inner casing and an exhaust outer casing, and the post-test mechanism comprises a post-test inner casing and a post-test outer casing; the exhaust inner casing and the rear test inner casing are assembled and combined, and the exhaust outer casing and the rear test outer casing are assembled and combined.
Furthermore, the front test inner casing and the front test outer casing are provided with contraction ends which are used for adjusting the radial size difference between the air inlet system flow channel and the test flow channel of the test assembly and have a guiding function; the range of the radial size difference of the contraction end is between the radial size of the outlet flow passage of the air inlet outer casing and the radial size of the outlet flow passage of the air inlet inner casing; the rear test inner casing and the rear test outer casing are provided with amplification sections for adjusting the radial dimension difference between the exhaust system flow passage and the test flow passage of the test assembly and expanding the radial dimension of the test flow passage so as to exhaust.
Furthermore, the contraction end and the test component are integrally formed into a structure; the amplification section and the test component are integrally formed.
Further, the radial size of the outlet flow channel of the air inlet outer casing is larger than that of the outlet flow channel of the air inlet inner casing; the radial size of an outlet flow channel of the air inlet outer casing is 300-100 mm; the radial size of the outlet flow channel of the air inlet inner casing is 150 mm-50 mm.
Further, the impeller disc is provided with a drum barrel, and the length of the drum barrel is adjusted to adapt to the axial change of the stacking line of the rotor system.
Further, the impeller disc is provided with a first elastic support piece on the front journal of the impeller disc for satisfying the rotor dynamic characteristics of different rotor systems and a second elastic support piece on the rear journal of the impeller disc for satisfying the rotor dynamic characteristics of different rotor systems.
Further, the first elastic supporting piece and the second elastic supporting piece are in squirrel-cage elastic supporting.
According to another aspect of the invention, a test method based on a modular turbine test piece is also provided, and the modular turbine test piece is adopted, and the test method comprises the following steps: when turbine test pieces under different flow channel parameters are subjected to simulation tests, the test assembly, the impeller disc and the guider which are matched are designed according to the flow channel parameters, the test assembly is installed between a shared air inlet system and an exhaust system, the impeller disc is installed in a shared rotor system except the impeller disc, the test assembly is fixedly connected with the guider, and the turbine test piece simulation tests are carried out.
The design method of the test assembly matched with the flow channel parameter design comprises the following steps: before adjustment, the size of a contraction end on the testing inner casing is adapted to the change of the flow channel parameters; or, the size of the shrinkage end on the front test outer box is adjusted to adapt to the change of the flow channel parameters; or simultaneously adjusting the sizes of the contraction end on the front test inner casing and the contraction end on the front test outer casing to adapt to the change of the flow channel parameters; after adjustment, the size of the amplification section on the test inner casing is adapted to the change of the flow channel parameters; or testing the size of the amplification section on the outer casing to adapt to the change of the flow channel parameters after adjustment; alternatively, the size of the amplification section on the post-test inner casing and the amplification section on the post-test outer casing are adjusted simultaneously to accommodate changes in the flow channel parameters.
Further comprising: when the axial direction of the rotor stacking changes, the axial direction change of the rotor stacking in different tests is realized by adjusting the length of a drum barrel of an impeller disc; when the rotor dynamic characteristics change, the rotor dynamic characteristics change in different tests through adopting the first elastic supporting piece and the second elastic supporting piece.
The invention has the following beneficial effects:
the invention relates to a modular turbine test piece, comprising: the test component can realize simulation tests of turbine test pieces under different flow channel parameters, and only matched test components, impeller discs and guides need to be designed based on the flow channel parameters and then assembled and combined under the condition of different flow channel parameters, namely the air inlet system, the exhaust system and the rotor system except the impeller discs are used as shared modules, and the test components, the impeller discs and the guides are used as replacement modules, so that the simulation tests of the turbine test pieces under different flow channel parameters are realized. In the prior art, even if the performance parameters of the test piece are close to those of the test piece similar to the overall structure, the flow channels of the turbine test pieces of different models are different due to the difference of the real flow channels of the turbines of different models, so that the flow channel piece is required to be designed and processed independently for each turbine test piece of different models, and the structure of the whole test piece is changed. The modularized turbine test piece provided by the invention can greatly reduce the processing cost, greatly shorten the design-processing-test period and obviously reduce the workload in the design and assembly processes. And, through sharing air intake system, exhaust system and the rotor system except that the impeller disc, reduced the part quantity of new processing, reduced the error accumulation of modularization turbine test piece, show the stability that improves modularization turbine test piece to realize quick assembly disassembly and change, improve the commonality of modularization turbine test piece.
In addition to the objects, features and advantages described above, other objects, features and advantages of the present invention are also provided. The present invention will be described in further detail below with reference to the accompanying drawings.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this application, illustrate embodiments of the invention and, together with the description, serve to explain the invention and not to limit the invention. In the drawings:
FIG. 1 is a schematic view of a prior art turbine test piece of the present invention;
FIG. 2 is a schematic view of a portion of a modular turbine test piece of a preferred embodiment of the present invention;
FIG. 3 is a schematic view of a modular turbine test piece inlet section flow path in accordance with a preferred embodiment of the present invention;
FIG. 4 is a schematic view of a flow path portion of an air inlet section of a modular turbine test piece in accordance with a preferred embodiment of the present invention; and
FIG. 5 is a schematic view of a portion of a rotor system according to a preferred embodiment of the present invention.
Description of reference numerals:
1. an air intake system; 11. an air inlet inner casing; 12. an air inlet outer casing; 2. an exhaust system; 3. a rotor system; 31. an impeller disc; 311. a drum; 312. a first elastic support member; 313. a second elastic support member; 4. a sealing system; 5. a lubricating oil system; 6. testing the component; 61. a front test mechanism; 611. testing the inner casing before; 612. testing the outer casing before; 613. a contracting end; 62. a working section testing mechanism; 63. a post-test mechanism; 631. testing the inner casing; 632. testing the outer casing; 633. an amplification section; 7. a guide device.
Detailed Description
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.
FIG. 1 is a schematic view of a prior art turbine test piece of the present invention; FIG. 2 is a schematic view of a portion of a modular turbine test piece of a preferred embodiment of the present invention; FIG. 3 is a schematic view of a modular turbine test piece inlet section flow path in accordance with a preferred embodiment of the present invention; FIG. 4 is a schematic view of a flow path portion of an air inlet section of a modular turbine test piece in accordance with a preferred embodiment of the present invention; FIG. 5 is a schematic view of a portion of a rotor system according to a preferred embodiment of the present invention.
As shown in fig. 2 and 5, the modular turbine test piece of the present embodiment includes: the device comprises an air inlet system 1, an exhaust system 2 and a rotor system 3, wherein a test component 6 which is coaxial with the air inlet system 1 and the exhaust system 2 and is used for realizing turbine test piece simulation tests under different flow channel parameters is arranged between the air inlet system 1 and the exhaust system 2; the rotor system 3 comprises an impeller disc 31 for adjusting the rotation work of the rotor system 3 according to different flow channel parameters, and a guider 7 for mutually matching with the impeller disc 31 and forming a working section of the modular turbine test piece. The invention relates to a modular turbine test piece, comprising: the air intake system 1, the exhaust system 2, the rotor system 3 and the test assembly 6, because the test assembly 6 can realize the turbine test piece simulation test under different runner parameters, when under the condition of different runner parameters, only the test assembly 6, the impeller disc 31 and the guider 7 which are matched need to be designed based on the runner parameters, and then the assembly combination is carried out, namely, the air intake system 1, the exhaust system 2 and the rotor system 3 except the impeller disc 31 are taken as a shared module, and the test assembly 6, the impeller disc 31 and the guider 7 are taken as a replacement module, thereby realizing the turbine test piece simulation test under different runner parameters. In the prior art, even if the performance parameters of the test piece are close to those of the test piece similar to the overall structure, the flow channels of the turbine test pieces of different models are different due to the difference of the real flow channels of the turbines of different models, so that the flow channel piece is required to be designed and processed independently for each turbine test piece of different models, and the structure of the whole test piece is changed. The modularized turbine test piece provided by the invention can greatly reduce the processing cost, greatly shorten the design-processing-test period and obviously reduce the workload in the design and assembly processes. And, through sharing air intake system 1, exhaust system 2, rotor system 3 and director 7 except that impeller dish 31, reduced the part quantity of new processing, reduced the error accumulation of modularization turbine test piece, show the stability that improves modularization turbine test piece to realize quick assembly disassembly and change, improve the commonality of modularization turbine test piece.
The modularized turbine test piece further comprises a sealing system 4 and an oil lubricating system 5. Preferably, the common module comprises an air intake system 1, an air exhaust system 2, a sealing system 4, an oil system 5 and a rotor system 3 other than the impeller disc 31. The number of newly machined parts is reduced. Preferably, the impeller disk 31 comprises a primary impeller disk and a secondary impeller disk, the guide 7 comprises a primary guide arranged between the rear end of the front test casing and the primary impeller disk, and a secondary guide arranged between the primary and secondary impeller disks to form a working section of the modular turbine test piece.
In this embodiment, the detachable connection for facilitating replacement of the testing component 6 under different flow channel parameters is adopted between the air intake system 1 and the testing component 6 and between the exhaust system 2 and the testing component 6. The detachable connection adopts one of ladder splicing opening connection, concave-convex connection or splicing. The air inlet system 1 and the testing component 6 and the air outlet system 2 and the testing component 6 are detachably connected, so that the assembly combination of the modularized turbine test piece is realized. The detachable connection is achieved through spigot positioning and bolt connection, and the test assembly 6 is firmly installed between the air inlet system 1 and the exhaust system 2.
As shown in fig. 2 and 3, in the present embodiment, the test assembly 6 includes a front test mechanism 61, a working section test mechanism 62, and a rear test mechanism 63, which are arranged in this order. The intake system 1 includes an intake inner casing 11 and an intake outer casing 12, and the front test mechanism 61 includes a front test inner casing 611 and a front test outer casing 612. The air inlet inner casing 11 and the front test inner casing 611 are assembled and combined, and the air inlet outer casing 12 and the front test outer casing 612 are assembled and combined. Exhaust system 2 includes an inner exhaust casing and an outer exhaust casing, and rear test mechanism 63 includes an inner rear test casing 631 and an outer rear test casing 632. The exhaust inner casing is assembled with the rear test inner casing 631, and the exhaust outer casing is assembled with the rear test outer casing 632.
The main functions of the air inlet system 1 and the exhaust system 2 are to realize the transition from the air inlet/exhaust of the vehicle platform to the test section, wherein the flow channel is contracted to the height required by the test after passing through the air inlet system 1, and is expanded from the height required by the test after passing through the exhaust system 2 so as to exhaust. The air intake and exhaust system 2 also has the functions of bearing force and supporting the rotor system 3 to rotate. In addition, the air inlet and exhaust system 2 is matched with the sealing system 4 and the lubricating oil system 5 to form a plurality of cavities, so that air pressure balancing, gas sealing and high-pressure gas leakage prevention are achieved, lubricating oil lubricating and cooling are provided for a bearing rotating at a high speed, lubricating oil is collected and discharged, and the like, and the test piece is a foundation stone. The testing assembly 6 comprises a front testing mechanism 61, a working section testing mechanism 62 and a rear testing mechanism 63, wherein the front testing mechanism 61 and the rear testing mechanism 63 finish the measurement of total inlet and outlet temperature, total air pressure, inner and outer wall static pressure and a flow field of the turbine test piece, and the working section testing mechanism 62 finishes the measurement of blade tip clearance and interstage static pressure.
In the present embodiment, as shown in fig. 2 and 3, the front inner test casing 611 and the front outer test casing 612 are provided with a constricted end 613 for adjusting the difference in radial dimension between the flow passage of the intake system 1 and the test flow passage of the test assembly 6 and having a guiding function. The convergent end 613 accommodates variations in radial dimension ranging between the radial dimension of the outlet flow path of the inlet outer casing 12 and the radial dimension of the outlet flow path of the inlet inner casing 11. Rear test inner casing 631 and rear test outer casing 632 are provided with an expansion section 633 for adjusting the difference in radial dimension of the exhaust system 2 flow passage and the test flow passage of test assembly 6 and expanding the radial dimension of the test flow passage for exhaust. Through research on the existing turbine test piece, the flow channel formed by the inlet system 1, the exhaust system 2 and the front and rear test systems of the turbine test piece is generally straight and unchanged. The ends of the inner and outer walls of the inlet outer casing 12 are already flush with the inner and outer walls of the previously tested inner and outer casings, i.e. at the outlet of the inlet casing assembly, the flow channel has been contracted to be consistent with the flow channel required by the test inlet, so that when the flow channel parameters are changed, the design and processing of the inlet and exhaust system 2 need to be re-expanded. The modular turbine test piece of the present invention has a contraction end 613 at one end of the front test inner casing 611 and the front test outer casing 612 close to the air intake system 1, and the flow channel enters the height required by the test after passing through the contraction end 613. Rear test inner casing 631 and rear test outer casing 632 are provided with amplification section 633, and the test flow path is amplified by amplification section 633 to discharge gas from exhaust system 2.
As shown in fig. 4, the flow channel outlets of the inlet inner casing 11 and the inlet outer casing 12 of the modular turbine test piece are no longer the starting point of the test flow channel, but are the upper and lower limits of the inlet flow channel of the modular turbine test piece of the type with similar parameters such as flow, power, rotation speed, etc. Similarly, the outlets of the inner exhaust casing and the outer exhaust casing of the exhaust system 2 are also the upper and lower limits of the outlet flow passage of the modular turbine test piece of this type. As shown in fig. 4, preferably, when the inlet flow path required for the test is changed from a to B, the inlet inner casing 11 and the inlet outer casing 12 are not changed, and the testing assembly 6 is replaced, and the flow path change is performed by the convergent end 613 on the front testing inner casing 611 and the front testing outer casing 612, and the expansion section 633 on the rear testing inner casing 631 and the rear testing outer casing 632.
In this embodiment, the contracting end 613 and the testing component 6 are integrally formed. The amplification stage 633 is of integral construction with the test assembly 6. The contracting end 613 and the testing component 6 as well as the amplifying section 633 and the testing component 6 are integrally formed, so that the structures of the contracting end 613 and the amplifying section 633 are centralized, the number of parts is reduced, a test piece is simplified, and the manufacturing cost is reduced.
As shown in fig. 2 and 3, in the present embodiment, the outlet flow passage radial dimension of the inlet outer casing 12 is larger than the outlet flow passage radial dimension of the inlet inner casing 11. The radial dimension of the outlet flow channel of the air inlet outer casing 12 is 300 mm-100 mm. The radial size of the outlet flow channel of the air inlet inner casing 11 is 150 mm-50 mm. The test flow channel in the test assembly 6 is an interval value between the radial size of the outlet flow channel of the air inlet outer casing 12 and the radial size of the outlet flow channel of the air inlet inner casing 11. Preferably, the radial dimension of the outlet flow channel of the air inlet outer casing 12 is 150mm, the radial dimension of the outlet flow channel of the air inlet inner casing 11 is 80mm, and the test flow channel is suitable for a modular turbine test piece with the test flow channel between 150mm and 80mm, and when a test is carried out, the flow channel change can be realized only by replacing the test component 6, the impeller replacing disc 3 and the guider 7 of the modular turbine test piece.
As shown in fig. 2 and 5, in the present embodiment, the impeller disc 31 is provided with a drum 311, and the length of the drum 311 is adjusted to adapt to the axial change of the stacking line of the rotor system 3. The rotor system 3 comprises a turbine shaft, a first-stage axial-flow stage impeller disc, a second-stage axial-flow stage blade disc, a bearing, a balance disc, an oil thrower disc, a sealing labyrinth and other parts, the air inlet system 1 and the exhaust system 2 provide support for the rotor system 3, the impeller disc 31 rotates to apply work under the drive of high-pressure gas, and the torque is transmitted out through the turbine shaft. The impeller disk 31 includes a second-stage axial-flow stage blade disk, and is applicable not only to a second-stage axial-flow stage blade but also to a third-stage axial-flow stage blade, a fourth-stage axial-flow stage blade disk, and the like. The impeller disc 31 is provided with a drum 311, and the length of the drum 311 is adjusted to adapt to the axial change of the stacking line of the rotor system 3. The rotor stacking axis refers to the central axis of the blade profile stacking on the impeller disc 31, and the axial change of the rotor stacking axis will cause the axial position change of the blades on the impeller disc 31 in the whole section of the flow passage. When the rotor stacking line changes axially, the length of the drum 311 of the replaced impeller disc 31 can be changed, so that the rotor stacking line changes axially in different tests.
As shown in fig. 2 and 3, in the present embodiment, the impeller disk 31 is provided with a first elastic support 312 on a front journal of the impeller disk 31 for satisfying the rotordynamic characteristics of different rotor systems 3 and a second elastic support 313 on a rear journal of the impeller disk 31 for satisfying the rotordynamic characteristics of different rotor systems 3. The rotor dynamics of the rotor system 3 will change with the structural change of the impeller disc 31, and in order to successfully perform the test, the instability of the rotor system 3 caused by the replacement of the impeller disc 31 needs to be reduced, and when the replaced impeller disc 31 is designed, the weight and the rotational inertia of the original impeller disc 31 are close to each other as much as possible, so that the stability of the rotor system 3 is ensured. The impeller disc 31 adopts a double-elastic support mode, and the first elastic support part 312 and the second elastic support part 313 are processed into a plurality of groups with different rigidity for standby, so that the rigidity of the first elastic support part 312 and the second elastic support part 313 can be flexibly adjusted by the modularized turbine test piece, and the structural stability of the rotor system 3 is ensured.
In this embodiment, the first elastic supporting member 312 and the second elastic supporting member 313 are supported by a squirrel cage elastic support. The first elastic supporting part 312 and the second elastic supporting part 313 are both made of squirrel-cage elastic supports, and one group of elastic supports with proper rigidity is selected for testing according to the influence of the newly replaced impeller disc 31 of the modularized turbine test piece on the rotation of the rotor system 3, so that the rotor dynamic characteristics of the rotor system 3 are guaranteed.
According to another aspect of the invention, a test method based on a modular turbine test piece is also provided, and the modular turbine test piece is adopted, and the test method comprises the following steps: when turbine test pieces under different flow channel parameters are subjected to simulation tests, the test component 6, the impeller disc 31 and the guider 7 which are matched with each other are designed according to the flow channel parameters, the test component 6 is installed between the shared air inlet system 1 and the shared exhaust system 2, the impeller disc 31 is installed in the shared rotor system 3 except for the impeller disc 31, and the test component 6 is fixedly connected with the guider 7 so as to perform the turbine test piece simulation tests. According to the using method of the modularized turbine test piece, the air inlet system 1, the air outlet system 2 and the rotor system 3 except the impeller disc 31 are used as common modules, and the flow channel change can be realized only by simply replacing the test component 6, the impeller disc 31 and the guider 7. The operation method of the modularized turbine test piece is easy, the installation work of the modularized turbine test piece can be completed once only by replacing the testing component 6, the impeller disc 31 and the guider 7, the design-processing-test period is greatly shortened, and the workload in the design and assembly process is remarkably reduced.
In this embodiment, the method for designing the matched test component 6 by using the flow channel parameter design includes: the size of the constriction 613 on the pre-test inner casing 611 is adjusted to accommodate changes in the channel parameters; alternatively, the size of the constriction 613 on the pre-test outer casing 612 is adjusted to accommodate changes in the channel parameters; alternatively, the size of the constriction 613 on the front inner test case 611 and the constriction 613 on the front outer test case 612 can be adjusted to accommodate the variation in the channel parameters; the size of the amplification section 633 on the adjusted test inner case 631 adapts to the changes in the flow channel parameters; alternatively, the size of the amplification section 633 on the outer casing 632 is adjusted to accommodate changes in the flow channel parameters; alternatively, the size of amplification section 633 on post-test inner casing 631 and amplification section 633 on post-test outer casing 632 are adjusted simultaneously to accommodate changes in flow path parameters. The contraction end 613 and the amplification section 633 are based on the design of the flow channel parameters, and have the advantages of high flexibility, convenient operation and wide application range.
In this embodiment, the method further includes: when the axial direction of the rotor stacking changes, the axial direction of the rotor stacking changes in different tests are realized by adjusting the length of the drum barrel 311 of the impeller disc 31. When the rotor dynamic characteristics are changed, the rotor dynamic characteristics are changed in different tests by adopting the first elastic supporting part 312 and the second elastic supporting part 313. The drum 311 and the first and second elastic supporting members 312 and 313 further improve the structural stability of the rotor system 3, and meet the change of the rotor dynamics of the rotor system 3 in the case of the change of the structure of the impeller disc 31.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (9)
1. A modular turbine test piece, comprising: an air inlet system (1), an air outlet system (2) and a rotor system (3), which is characterized in that,
a test component (6) which is coaxial with the air inlet system (1) and the exhaust system (2) and is used for realizing turbine test piece simulation tests under different flow channel parameters is arranged between the air inlet system (1) and the exhaust system (2), detachable connections which are used for realizing replacement of the test component (6) under different flow channel parameters are adopted between the air inlet system (1) and the test component (6) and between the exhaust system (2) and the test component (6), and the detachable connections adopt one of stepped splicing port connection, concave-convex connection or splicing connection;
the testing assembly (6) comprises a front testing mechanism (61), a working section testing mechanism (62) and a rear testing mechanism (63) which are sequentially arranged, the front testing mechanism (61) and the rear testing mechanism (63) finish the measurement of total inlet and outlet temperature, total air pressure, inner and outer wall static pressure and a flow field of the turbine test piece, and the working section testing mechanism (62) finishes the measurement of blade tip clearance and interstage static pressure;
the air inlet system (1) comprises an air inlet inner casing (11) and an air inlet outer casing (12), the front testing mechanism (61) comprises a front testing inner casing (611) and a front testing outer casing (612), the air inlet inner casing (11) and the front testing inner casing (611) are assembled and combined, the air inlet outer casing (12) and the front testing outer casing (612) are assembled and combined, the air outlet system (2) comprises an air outlet inner casing and an air outlet outer casing, the rear testing mechanism (63) comprises a rear testing inner casing (631) and a rear testing outer casing (632), the air outlet inner casing and the rear testing inner casing (631) are assembled and combined, and the air outlet outer casing and the rear testing outer casing (632) are assembled and combined;
the front inner testing casing (611) and the front outer testing casing (612) are provided with a contraction end (613) which is used for adjusting the radial size difference of the inlet system (1) flow channel and the testing flow channel of the testing component (6) and has a guiding effect, the contraction end (613) adjusts the radial size difference in a range between the radial size of the outlet flow channel of the inlet outer casing (12) and the radial size of the outlet flow channel of the inlet inner casing (11), and the rear inner testing casing (631) and the rear outer testing casing (632) are provided with an expansion section (633) which is used for adjusting the radial size difference of the exhaust system (2) flow channel and the testing flow channel of the testing component (6) and expanding the radial size of the testing flow channel so as to exhaust;
the rotor system (3) comprises an impeller disc (31) for adjusting the rotor system (3) to rotate and apply work according to different flow channel parameters;
a guide (7) for co-operating with the impeller disc (31) and forming a working section of the modular turbine test piece.
2. The modular turbine test piece of claim 1,
the contraction end (613) and the test component (6) are integrally formed into a structure;
the amplification section (633) is of an integral structure with the test component (6).
3. The modular turbine test piece of claim 1,
the radial size of an outlet flow channel of the air inlet outer casing (12) is larger than that of an outlet flow channel of the air inlet inner casing (11);
the radial size of an outlet flow channel of the air inlet outer casing (12) is 300-100 mm;
the radial size of an outlet flow channel of the air inlet inner casing (11) is 150-50 mm.
4. The modular turbine test piece of claim 1,
the impeller disc (31) is provided with a drum barrel (311), and the length of the drum barrel (311) is adjusted to adapt to the axial change of the stacking line of the rotor system (3).
5. The modular turbine test piece of claim 4,
the impeller disc (31) is provided with a first elastic supporting piece (312) which is arranged on a front journal of the impeller disc (31) and is used for meeting the rotor dynamic characteristics of different rotor systems (3) and a second elastic supporting piece (313) which is arranged on a rear journal of the impeller disc (31) and is used for meeting the rotor dynamic characteristics of different rotor systems (3).
6. The modular turbine test piece of claim 5,
the first elastic supporting piece (312) and the second elastic supporting piece (313) adopt squirrel-cage elastic supporting.
7. A modular turbine test piece-based testing method using the modular turbine test piece of any one of claims 1 to 6, comprising the steps of:
during turbine test piece simulation tests under different flow channel parameters, the test component (6), the impeller disc (31) and the guider (7) which are matched with each other are designed according to the flow channel parameters, the test component (6) is installed between the shared air inlet system (1) and the shared air exhaust system (2), the impeller disc (31) is installed in the shared rotor system (3) except for the impeller disc (31), and the test component (6) is fixedly connected with the guider (7) to perform the turbine test piece simulation tests.
8. The modular turbine test piece-based test method of claim 7, wherein the design method of the test assembly (6) designed to match by flow channel parameters comprises:
adjusting the size of the constriction (613) on the pre-test inner casing (611) to accommodate changes in the channel parameters; or
Adjusting the size of a constriction (613) on the pre-test outer casing (612) to accommodate changes in the flow channel parameters; or
Simultaneously adjusting the size of the convergent end (613) on the front test inner casing (611) and the convergent end (613) on the front test outer casing (612) to accommodate changes in the flow channel parameters;
adjusting the size of the amplification section (633) on the test inner casing (631) to accommodate changes in the flow channel parameters; or
Testing the size of the amplified section (633) on the outer casing (632) after adjustment to accommodate changes in the flow channel parameters; or
The size of the amplification section (633) on the post-test inner casing (631) and the amplification section (633) on the post-test outer casing (632) are adjusted simultaneously to accommodate the change in the flow channel parameters.
9. The modular turbine test piece-based test method of claim 7, further comprising
When the axial direction of the rotor stacking changes, the axial direction change of the rotor stacking in different tests is realized by adjusting the length of a drum barrel (311) of the impeller disc (31);
when the rotor dynamic characteristic changes, the first elastic supporting piece (312) and the second elastic supporting piece (313) are adopted to meet the requirement of the rotor dynamic characteristic changes in different tests.
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| CN112414720A (en) * | 2020-11-23 | 2021-02-26 | 东方电气集团东方汽轮机有限公司 | Gas turbine secondary air system rotation test device and test method |
| CN112432793A (en) * | 2020-11-23 | 2021-03-02 | 东方电气集团东方汽轮机有限公司 | Gas turbine wheel disc air extraction test piece and modeling test parameter design method |
| CN114491915B (en) * | 2021-10-20 | 2023-06-30 | 中国航发四川燃气涡轮研究院 | Bearing performance analysis method considering rotor and spring bearing influence |
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