CN112524383B - Axial expansion self-compensating device for aircraft engine turbine part tester - Google Patents
Axial expansion self-compensating device for aircraft engine turbine part tester Download PDFInfo
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- CN112524383B CN112524383B CN202011289888.7A CN202011289888A CN112524383B CN 112524383 B CN112524383 B CN 112524383B CN 202011289888 A CN202011289888 A CN 202011289888A CN 112524383 B CN112524383 B CN 112524383B
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- shell section
- turning shell
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- turbine
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16L—PIPES; JOINTS OR FITTINGS FOR PIPES; SUPPORTS FOR PIPES, CABLES OR PROTECTIVE TUBING; MEANS FOR THERMAL INSULATION IN GENERAL
- F16L51/00—Expansion-compensation arrangements for pipe-lines
- F16L51/04—Expansion-compensation arrangements for pipe-lines making use of bends, e.g. lyre-shaped
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/02—Details or accessories of testing apparatus
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Gasket Seals (AREA)
Abstract
The invention belongs to the field of mechanical design, and particularly relates to an axial expansion self-compensation device for an annular flow channel steering component under the conditions of high temperature and high pressure. The method comprises the following steps: the turbine test device comprises an inner turning shell section and an outer turning shell section, wherein the inner turning shell section and the outer turning shell section are both of annular structures, one ends of the inner turning shell section and the outer turning shell section are connected with a turbine test piece, and the other ends of the inner turning shell section and the outer turning shell section are connected with an exhaust volute or an intake volute; the outer ring is in bolted connection with the inner turning shell section and the outer turning shell section, and the inner turning shell section and the outer turning shell section are respectively in sealed connection with the turbine test piece through extrusion of the outer pressing ring on the sealing rings. The invention avoids using an expansion joint, so that the axial length is shorter, and the application environment of the device is greatly widened.
Description
Technical Field
The invention belongs to the field of mechanical design, and particularly relates to an axial expansion self-compensation device for an annular flow channel steering component under the conditions of high temperature and high pressure.
Background
In the application, test and related industries of aeroengines, gas turbines and flue gas turbines, sometimes a high-temperature and high-pressure fluid channel needs to be steered, and a part for steering needs to have the functions of connection and steering and also needs to have the function of absorbing axial expansion of the channel so as to ensure that the channel can safely operate under various working conditions.
Disclosure of Invention
The purpose of the invention is as follows:
the utility model provides an axial expansion self compensating device for aeroengine turbine part tester, solve high temperature high pressure and turn to defects such as the common structure of part application scene is limited, the flexibility ratio is low, the installation is dismantled loaded down with trivial details, promote life simultaneously, reduce design, processing, maintenance cost, provide the steering part that can expand self compensating for the high temperature high pressure fluid matter in all kinds of industry.
The technical scheme is as follows:
in a first aspect, there is provided an axial expansion self-compensating device for an aircraft engine turbine component tester, comprising: the turbine test device comprises an inner turning shell section and an outer turning shell section, wherein the inner turning shell section and the outer turning shell section are both of annular structures, one ends of the inner turning shell section and the outer turning shell section are connected with a turbine test piece, and the other ends of the inner turning shell section and the outer turning shell section are connected with an exhaust volute or an intake volute; the outer ring is in bolted connection with the inner turning shell section and the outer turning shell section, and the inner turning shell section and the outer turning shell section are respectively in sealed connection with the turbine test piece through extrusion of the outer pressing ring on the sealing rings.
Further, the annular sealing ring is a metal sealing ring.
Further, the annular sealing ring is a graphite packing.
In a second aspect, there is provided an axial expansion self-compensating device for an aircraft engine turbine component tester, comprising: the turbine test device comprises an inner turning shell section and an outer turning shell section, wherein the inner turning shell section and the outer turning shell section are both of annular structures, one ends of the inner turning shell section and the outer turning shell section are connected with a turbine test piece, and the other ends of the inner turning shell section and the outer turning shell section are connected with an exhaust volute or an intake volute; the outer ring is in bolted connection with the inner turning shell section and the outer turning shell section, and the inner turning shell section and the outer turning shell section are in sealed connection with the exhaust volute or the air inlet volute through extrusion of the outer pressing ring on the sealing rings.
Further, the annular sealing ring is a metal sealing ring.
Further, the annular sealing ring is a graphite packing.
In a third aspect, there is provided an axial expansion self-compensating device for an aircraft engine turbine component tester, comprising: the turbine test device comprises an inner turning shell section and an outer turning shell section, wherein the inner turning shell section and the outer turning shell section are both of annular structures, one ends of the inner turning shell section and the outer turning shell section are connected with a turbine test piece, and the other ends of the inner turning shell section and the outer turning shell section are connected with an exhaust volute or an intake volute; wherein, the inner turning shell section and the outer turning shell section are respectively divided into a front section and a rear section, the joints of the front section and the rear section are respectively provided with an annular sealing ring, the outer side of each annular sealing ring is provided with an outer annular ring, each outer annular ring is respectively connected with the inner turning shell section or the outer turning shell section through bolts, and the front section and the rear section are hermetically connected through the extrusion of the outer annular rings on the sealing rings.
Further, the annular sealing ring is a metal sealing ring.
Further, the annular sealing ring is a graphite packing.
Further, the annular sealing ring is a rubber sealing ring.
Has the advantages that:
the axial expansion self-compensating device for the annular flow passage steering component, which is designed by the invention, has a pressure-resistant range which is obviously higher than that of the traditional thin-wall structure, and can reliably work within the range of 5kPaA to 1000 kPaA; the rigidity is high, the natural frequency is low, and the shock of high-speed fluid hardly excites the vibration of the steering shell, so that the fatigue damage caused by vibration is avoided, and the service life of a steering component is prolonged; because the plug-in extrusion sealing structure is adopted, the front section of the outer steering shell and the front section of the inner steering shell can move along the axial direction, the axial length of the steering component can be adjusted on the premise of ensuring the sealing effect, and the steering component is suitable for steering objects in a certain geometric dimension range and has certain flexibility; loosen the clamping ring, can promote outer shell anterior segment that turns to and interior shell anterior segment that turns to along axial displacement certain distance, reserve considerable space for the object that needs to connect to turn to, be favorable to reducing the installation of relevant equipment and dismantle intensity of labour and work load. The expansion joint is avoided, the axial length is shorter, and the application environment of the device is greatly widened.
Drawings
FIG. 1 is a schematic representation of an annular flow channel diverter component according to the prior art;
FIG. 2 is a schematic of an annular flow diverter component of thin-walled construction according to the prior art;
FIG. 3 is a schematic of an annular flow channel diverter component with an expansion joint according to the prior art;
FIG. 4 is a cross-sectional view of an annular flow channel diverter component axial expansion self-compensating device according to an embodiment of the present invention;
FIG. 5 is an enlarged view of I-I in FIG. 4;
FIG. 6 is an enlarged view of II-II in FIG. 4.
Wherein, 1-outer turn to casing anterior segment 2-interior turn to casing anterior segment 3-outer turn to casing back end 4-interior turn to casing back end 5-outer snap ring 6-outer ring metal O type circle 7-inner ring compression ring 8-inner ring metal O type circle.
Detailed Description
The annular flow path diverter element typically comprises an inner and an outer diverter segment, shown in the general form of figure 1.
The high-temperature high-pressure steering component popular in the market at present mainly adopts two modes: one is formed by welding thin-wall steel plates with the wall thickness not more than 2mm, and the axial expansion of the test piece is absorbed by the deformation of the thin-wall piece, as shown in figure 2. Secondly, a thick-wall steel plate with the wall thickness exceeding 5mm is used, and an expansion joint is additionally arranged at the front end of the steering section to absorb the axial expansion of the runner, as shown in figure 3.
The main limitations of the structure shown in fig. 2 are: due to the use of thin-walled parts, the strength of the material limits the operating conditions. There are practical surfaces where the steering member is plastically deformed when the fluid pressure is above 350kPaA or below 20 kPaA. In addition, when the flow velocity of the fluid is high, the component is easy to vibrate, the component can be damaged due to fatigue after long-time operation, and the use cost and the potential safety hazard are increased.
Since the geometry of the part using the structure is fixed, the geometry of the connected steering objects of the part must also be fixed, so that the structure cannot be applied to connected steering objects of various sizes, which cannot be satisfied for a use scene requiring a certain flexibility.
The structure shown in fig. 3 can avoid the problems of poor bearing capacity and easy fatigue damage of the first structure, but the axial length is increased due to the additional arrangement of the expansion joint, and the structure cannot be applied to application scenes with requirements on certain spaces or without permission of increasing the axial length. Similarly, as with the first configuration, the part, if it is to be geometrically flexible, requires multiple different sizes of the part and does not allow for infinite adjustment of the axial length.
One embodiment of the invention is that the outer steering shell section is divided into an outer steering shell front section and an outer steering shell rear section, the inner steering shell section is divided into an inner steering shell front section and an inner steering shell rear section, all components are in thick-wall structures for bearing capacity, and if the required bearing strength is further improved, a plurality of rib plates can be additionally arranged to connect the outer steering shell rear section and the inner steering shell rear section into a whole.
The connecting flanges of the front section and the rear section of the outer steering shell are respectively connected with the outer shell of the annular runner which needs to be steered, and the connecting flanges of the front section and the rear section of the inner steering shell are respectively connected with the inner shell of the annular runner which needs to be steered. The butt joint end of the front section of the outer steering shell is provided with a small section of straight section which is inserted into the butt joint end of the rear section of the outer steering shell, a sealing ring is arranged between the small section of straight section and the butt joint end of the rear section of the outer steering shell, and the sealing ring is extruded by a pressing ring to be tightly attached to the front section and the rear section of the outer steering shell, so that the sealing effect of the outer steering shell is ensured; similarly, the butt joint end of the inner steering shell front section is also designed with a small section straight section, the inner steering shell rear section butt joint end is inserted into the inner steering shell, a sealing ring is arranged between the inner steering shell rear section butt joint end and the inner steering shell rear section butt joint end, the sealing ring is extruded by the pressing ring, the inner steering shell front section and the inner steering shell rear section are tightly attached to the sealing ring, the sealing effect of the inner steering shell is ensured, and the whole device can be installed.
When annular runner takes place axial expansion, drive outer shell anterior segment that turns to and interior shell anterior segment that turns to do axial displacement in outer shell back end that turns to and interior switching back end respectively, guarantee sealed effect by clamping ring extrusion sealing ring simultaneously to this completion absorbs annular runner axial expansion and turns to the purpose.
When the annular runner is disassembled, the pressing ring is only required to be loosened, the outer steering shell front section and the inner steering shell front section can move for a certain distance along the axial direction of the annular runner, a certain space is developed for disassembling the relevant parts of the annular runner, and therefore the assembling and disassembling processes of the relevant parts of the annular runner are simplified.
In the embodiment shown in fig. 4 to 6, the flange of the front section 1 of the outer turning shell is connected with the flange surface of the outer ring of the annular flow passage component, and the flange of the front section 2 of the inner turning shell is connected with the flange surface of the inner ring of the annular flow passage component; similarly, the flange of the rear section 3 of the outer steering shell and the flange of the rear section 4 of the inner steering shell are respectively connected with the flange surfaces of the outer ring and the inner ring of the steered annular runner component. Inserting the straight section of the outer steering shell 1 into the butt joint end of the rear section 3 of the outer steering shell, installing an outer ring metal O-shaped ring 6 between the straight section and the butt joint end, and extruding the outer ring metal O-shaped ring 6 by using an outer pressure ring 5 to enable the outer ring metal O-shaped ring to be tightly attached to the front section 1 of the outer steering shell and the rear section 3 of the outer steering shell to finish sealing; similarly, the straight section of the inner steering shell front section 2 is inserted into the butt joint end of the inner steering shell 4, an inner ring metal O-shaped ring 8 is arranged between the straight section and the butt joint end of the inner steering shell front section 2, the inner ring metal O-shaped ring 8 is extruded by the inner compression ring 7, the inner steering shell front section 2 and the inner steering shell rear section 4 are tightly attached to the inner steering shell front section 2 and the inner steering shell rear section 4, and sealing and installation of the whole device are completed.
When the annular flow passage expands, the outer steering shell front section 1 and the inner steering shell front section 2 can respectively move in the outer steering shell rear section 3 and the inner switching rear section 4 along the axial direction under the driving of the outer steering shell front section 1 and the inner steering shell front section 2, so that the purpose of absorbing the axial expansion of the annular flow passage is achieved.
During dismounting device, loosen outer clamping ring 5 and inner clamping ring 7, turn to shell anterior segment 1 outward and turn to shell anterior segment 3 with the interior and can follow one section distance of axial displacement, conveniently connect the installation of object and dismantle.
When the annular flow channel equipment with different lengths is connected, the outer steering shell front section 1 and the inner steering shell front section 3 can be properly moved, so that the total length of the device is changed, and the device can be suitable for the annular flow channel equipment with different axial lengths in a certain periphery.
In another embodiment of the present invention, a straight segment plus seal ring and pressure ring structure may be applied to the location of connection with the inlet volute.
In yet another embodiment of the present invention, a straight segment plus seal ring and pressure ring configuration may be applied in place of attachment to the exhaust volute. The two embodiments only need to change the connection mode of the steering shell section and the air inlet volute or the air exhaust volute, the steering shell section does not need to be split into two parts, and the structure is simpler.
The axial expansion self-compensating device for the annular flow passage steering component designed by the invention is implemented in an exhaust structure of a certain aircraft engine turbine component tester, and the tester can bear a plurality of turbine component tests. Practice has shown that the exhaust structure using the invention has at least the following advantages:
a) the pressure-resistant range is obviously higher than that of the traditional thin-wall structure, and the pressure-resistant structure can reliably work within the range of 5kPaA to 1000 kPaA;
b) the rigidity is high, the natural frequency is low, and the shock of high-speed fluid hardly excites the vibration of the steering shell, so that the fatigue damage caused by vibration is avoided, and the service life of a steering component is prolonged;
c) because the plug-in extrusion sealing structure is adopted, the front section of the outer steering shell and the front section of the inner steering shell can move along the axial direction, the axial length of the steering component can be adjusted on the premise of ensuring the sealing effect, and the steering component is suitable for steering objects in a certain geometric dimension range and has certain flexibility;
d) loosen the clamping ring, can promote outer shell anterior segment that turns to and interior shell anterior segment that turns to along axial displacement certain distance, reserve considerable space for the object that needs to connect to turn to, be favorable to reducing the installation of relevant equipment and dismantle intensity of labour and work load.
e) The expansion joint is avoided, the axial length is shorter, and the application environment of the device is greatly widened.
The device can be used in the high-temperature high-pressure fluid annular flow channel of aeroengines, gas turbines and flue gas turbine tests, applications and related industries when the high-temperature high-pressure fluid annular flow channel needs to be turned, so that the fluid turning is realized, and the axial expansion is compensated.
Claims (10)
1. An axial expansion self-compensating device for an aircraft engine turbine component tester, comprising: the turbine test device comprises an inner turning shell section and an outer turning shell section, wherein the inner turning shell section and the outer turning shell section are both of annular structures, one ends of the inner turning shell section and the outer turning shell section are connected with a turbine test piece, and the other ends of the inner turning shell section and the outer turning shell section are connected with an exhaust volute or an intake volute; the turbine test piece comprises an inner turning shell section, an outer turning shell section and a turbine test piece, wherein an annular groove is formed in the outer side of the joint of one end of the inner turning shell section and one end of the outer turning shell section, the joint is connected with the turbine test piece, an annular sealing ring is arranged in the annular groove, an inner pressing ring is arranged on the inner turning shell section, an outer pressing ring is arranged on the outer turning shell section, the inner pressing ring and the outer pressing ring are respectively in bolted connection with the inner turning shell section and the outer turning shell section, and the inner turning shell section and the outer turning shell section are respectively in sealed connection with the turbine test piece through extrusion of the inner pressing ring and the outer pressing ring on the sealing rings.
2. The device of claim 1, wherein the annular seal is a metal seal.
3. The apparatus of claim 1 wherein the annular seal ring is a graphite packing.
4. An axial expansion self-compensating device for an aircraft engine turbine component tester, comprising: the turbine test device comprises an inner turning shell section and an outer turning shell section, wherein the inner turning shell section and the outer turning shell section are both of annular structures, one ends of the inner turning shell section and the outer turning shell section are connected with a turbine test piece, and the other ends of the inner turning shell section and the outer turning shell section are connected with an exhaust volute or an intake volute; the exhaust turbine shell or the intake turbine shell is characterized in that an annular groove is formed in the outer side of the joint of one end of the inner turning shell section and one end of the outer turning shell section with the exhaust turbine shell or the intake turbine shell, an annular sealing ring is arranged in the annular groove, an inner pressing ring is arranged on the inner turning shell section, an outer pressing ring is arranged on the outer turning shell section, the inner pressing ring and the outer pressing ring are respectively in bolted connection with the inner turning shell section and the outer turning shell section, and the inner turning shell section and the outer turning shell section are in sealed connection with the exhaust turbine shell or the intake turbine shell through extrusion of the sealing rings by the inner pressing ring and the outer pressing ring.
5. The device of claim 4, wherein the annular seal is a metal seal.
6. The apparatus of claim 4 wherein the annular seal ring is a graphite packing.
7. An axial expansion self-compensating device for an aircraft engine turbine component tester, comprising: the turbine test device comprises an inner turning shell section and an outer turning shell section, wherein the inner turning shell section and the outer turning shell section are both of annular structures, one ends of the inner turning shell section and the outer turning shell section are connected with a turbine test piece, and the other ends of the inner turning shell section and the outer turning shell section are connected with an exhaust volute or an intake volute; wherein, interior turn to the shell section and outer turn to the shell section and divide into anterior segment and back end respectively, be provided with ring packing respectively in anterior segment and back end junction, the ring packing outside of interior turn to the shell section all is provided with interior clamping ring, the ring packing outside of outer turn to the shell section is provided with the outer clamping ring, interior clamping ring and outer clamping ring respectively with interior turn to shell section or outer turn to shell section bolted connection, make anterior segment and back end sealing connection through the extrusion of interior clamping ring and outer clamping ring to the sealing washer.
8. The apparatus of claim 7, wherein the annular seal is a metal seal.
9. The apparatus of claim 7 wherein the annular seal ring is a graphite packing.
10. The device of claim 7, wherein the annular seal is a rubber seal.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011289888.7A CN112524383B (en) | 2020-11-17 | 2020-11-17 | Axial expansion self-compensating device for aircraft engine turbine part tester |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011289888.7A CN112524383B (en) | 2020-11-17 | 2020-11-17 | Axial expansion self-compensating device for aircraft engine turbine part tester |
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| Publication Number | Publication Date |
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| CN112524383A CN112524383A (en) | 2021-03-19 |
| CN112524383B true CN112524383B (en) | 2022-04-19 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202011289888.7A Active CN112524383B (en) | 2020-11-17 | 2020-11-17 | Axial expansion self-compensating device for aircraft engine turbine part tester |
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| CN1094121A (en) * | 1993-03-25 | 1994-10-26 | Abb管理有限公司 | Radial-flow exhaust turbocharger turbine |
| CN101960113A (en) * | 2008-03-13 | 2011-01-26 | 博格华纳公司 | Exhaust manifold of an internal combustion engine |
| CN102395768A (en) * | 2009-04-20 | 2012-03-28 | 博格华纳公司 | Simplified variable geometry turbocharger with variable volute flow volumes |
| CN108760323A (en) * | 2018-05-29 | 2018-11-06 | 中国航发湖南动力机械研究所 | Compensation of pipeline device and its turbine test device |
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| DE10138056A1 (en) * | 2001-08-03 | 2003-02-13 | Atlas Copco Energas | turbomachinery |
| CN101506476B (en) * | 2006-08-24 | 2011-09-14 | Abb涡轮系统有限公司 | Turbine housing |
| DE102009054403A1 (en) * | 2009-11-24 | 2011-05-26 | Bosch Mahle Turbo Systems Gmbh & Co. Kg | turbocharger |
| US20120216608A1 (en) * | 2011-02-25 | 2012-08-30 | General Electric Company | System for measuring parameters of fluid flow in turbomachinery |
| US10151215B2 (en) * | 2015-06-01 | 2018-12-11 | Solar Turbines Incorporated | High speed recorder for a gas turbine engine |
| CN106678476A (en) * | 2017-02-20 | 2017-05-17 | 江苏丰禾机械制造股份有限公司 | Sleeve-type dynamic seal compensator |
| CN207195934U (en) * | 2017-08-20 | 2018-04-06 | 许月进 | It is a kind of to import and export vertical free-standing compact expansion joint |
| CN109707945B (en) * | 2018-12-05 | 2021-12-28 | 洛阳双瑞特种装备有限公司 | High-temperature-resistant high-pressure compensator |
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2020
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Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1094121A (en) * | 1993-03-25 | 1994-10-26 | Abb管理有限公司 | Radial-flow exhaust turbocharger turbine |
| CN101960113A (en) * | 2008-03-13 | 2011-01-26 | 博格华纳公司 | Exhaust manifold of an internal combustion engine |
| CN102395768A (en) * | 2009-04-20 | 2012-03-28 | 博格华纳公司 | Simplified variable geometry turbocharger with variable volute flow volumes |
| CN108760323A (en) * | 2018-05-29 | 2018-11-06 | 中国航发湖南动力机械研究所 | Compensation of pipeline device and its turbine test device |
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| CN112524383A (en) | 2021-03-19 |
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