CN108708789B - Gas turbine support structure - Google Patents
Gas turbine support structure Download PDFInfo
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- CN108708789B CN108708789B CN201810927012.7A CN201810927012A CN108708789B CN 108708789 B CN108708789 B CN 108708789B CN 201810927012 A CN201810927012 A CN 201810927012A CN 108708789 B CN108708789 B CN 108708789B
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- 230000008093 supporting effect Effects 0.000 claims abstract description 30
- 239000003921 oil Substances 0.000 claims description 75
- 239000002199 base oil Substances 0.000 claims description 2
- 238000004364 calculation method Methods 0.000 description 3
- 238000006073 displacement reaction Methods 0.000 description 2
- 238000010438 heat treatment Methods 0.000 description 2
- 239000010687 lubricating oil Substances 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000002035 prolonged effect Effects 0.000 description 2
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/20—Mounting or supporting of plant; Accommodating heat expansion or creep
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Pivots And Pivotal Connections (AREA)
- Engine Equipment That Uses Special Cycles (AREA)
Abstract
The invention discloses a gas turbine supporting structure, wherein a cold end support supports the weight of the cold end of a gas turbine, and a hot end support supports the weight of the hot end of the gas turbine; the hot end support comprises a left hot end connecting rod and a right hot end connecting rod; the upper end and the lower end of the right hot end connecting rod are respectively connected with the right side of the base and the gas turbine by adopting spherical hinges, the spherical hinge connection center of the right hot end connecting rod and the gas turbine is used as an upper right fulcrum, and the spherical hinge connection center meter of the right hot end connecting rod and the base is used as a lower right fulcrum; the axes of the left hot end connecting rod and the right hot end connecting rod are in the same hot end supporting plane, and the left hot end connecting rod and the right hot end connecting rod are symmetrically distributed on the left side and the right side of the gas turbine; when the temperatures of the cold end and the hot end of the gas turbine are the same, the included angle between the connecting line of the upper right fulcrum and the hot center point and the axis of the right hot end connecting rod is 90.01-91.00 degrees; the thermal center point is the intersection point of the gas turbine axis and the hot end support plane. The gas turbine supporting structure can ensure that the central axis does not generate angular offset after the hot end of the whole gas turbine is heated and expanded.
Description
Technical Field
The invention belongs to the technical field of gas turbines, and particularly relates to a gas turbine supporting structure.
Background
A Gas Turbine (Gas Turbine) is a rotary power machine which uses continuously flowing Gas as a working medium to convert the heat energy of the working medium into mechanical work. Compared with the traditional internal combustion engine, the engine has the advantages of simple structure, small volume, light weight and the like under the same power, and is widely applied to the fields of energy, electric power, ships, military and the like. For the support of the gas turbine, a two-section or three-section support mode is generally adopted, the two-section support is generally used for a radial flow gas turbine with smaller axial dimension, the two-section refers to a cold end support section and a hot end support section, the three-section support is generally used for an axial flow gas turbine with larger axial dimension, and the three-section refers to an additional middle auxiliary support section besides the cold end support section and the hot end support section. The cold end support and the hot end support together bear the weight of the gas turbine body and additional loads in operation. The cold end support generally limits gas turbine axial and lateral displacement, so the cold end cross section is also called a "dead center" position. The hot end support, in addition to serving as a support, also allows free expansion of the gas turbine in the axial and radial directions.
The existing support has the following problems: after the hot end of the gas turbine expands under the working and heating conditions, the central point of the gas turbine in the supporting section of the hot end deviates, while the central point in the supporting section of the cold end remains unchanged, and finally the central axis of the whole gas turbine deviates in an angular direction. Because the gas turbine has very high coaxiality requirement with the axis of the driven equipment, the axial connecting piece and the bearing are subjected to offset load after the central axis of the gas turbine is subjected to angular offset, and if the offset load is too large, the connecting piece or the bearing is directly damaged, so that the service life of the connecting piece or the bearing is at least reduced.
Disclosure of Invention
The invention aims to solve the technical problem of providing a gas turbine supporting structure which can ensure that the central axis of the whole gas turbine does not generate angular deviation after being heated and expanded.
In order to solve the technical problems, the gas turbine supporting structure provided by the invention comprises a cold end support and a hot end support;
the cold end support is fixed on the base and used for supporting the cold end weight of the gas turbine;
the hot end support is fixed on the base and used for supporting the weight of the hot end of the gas turbine;
the hot end support comprises a left hot end connecting rod and a right hot end connecting rod;
the lower end of the right hot end connecting rod is connected with the base by adopting a spherical hinge, the upper end of the right hot end connecting rod is connected to the right side of the gas turbine by adopting a spherical hinge, and the spherical hinge connecting center of the right hot end connecting rod and the gas turbine is used as an upper right fulcrum; the right hot end connecting rod is connected with the spherical hinge of the base to be used as a right lower fulcrum by the central meter;
the axes of the left hot end connecting rod and the right hot end connecting rod are in the same hot end supporting plane, and the left hot end connecting rod and the right hot end connecting rod are symmetrically distributed on the left side and the right side of the gas turbine;
when the temperatures of the cold end and the hot end of the gas turbine are the same, the included angle between the connecting line of the upper right fulcrum and the hot center point and the axis of the right hot end connecting rod is 90.01-91.00 degrees;
the thermal center point is the intersection point of the gas turbine axis and the hot end support plane.
Preferably, the hot end support further comprises a transverse pull rod;
the upper end of the transverse pull rod is connected with the middle position of the bottom surface of the hot end of the gas turbine by adopting a spherical hinge, and the lower end of the transverse pull rod is connected with a base at the lower end of the right hot end connecting rod or the left hot end connecting rod by adopting a spherical hinge.
Preferably, the cold end support comprises a left cold end connecting rod and a right cold end connecting rod;
the lower end of the right cold end connecting rod is connected with the base by adopting a spherical hinge, and the upper end of the right cold end connecting rod is connected to the right side of the gas turbine by adopting a spherical hinge;
the axes of the left cold end connecting rod and the right cold end connecting rod are in the same cold end supporting plane, and the left cold end connecting rod and the right cold end connecting rod are symmetrically distributed on the left side and the right side of the gas turbine.
Preferably, the gas turbine support structure further comprises an oil return pipe and an oil return sleeve;
the oil return pipe is fixed on an oil return port of the gearbox of the gas turbine;
the oil return sleeve is fixed on an oil inlet of an oil tank of the base;
the oil return pipe and the oil return sleeve are round pipes, the outer diameter of the oil return pipe is smaller than or equal to the inner diameter of the oil return sleeve, the oil return pipe and the oil return sleeve are connected in a cylindrical sleeve mode, and the oil return pipe can axially slide or circumferentially rotate in the oil return sleeve;
the matching surface of the oil return pipe and the oil return sleeve is provided with an oil seal.
Preferably, the oil return pipe is fixed on an oil return port of the gearbox of the gas turbine through a bolt;
the oil return sleeve is fixed on an oil inlet of the base oil tank through a bolt;
the oil return port of the gas turbine gearbox is positioned at the cold end of the gas turbine.
Preferably, the right hot end connecting rod and the spherical hinge connecting center of the gas turbine are equal in height with the spherical hinge connecting center of the gas turbine.
Preferably, when the temperatures of the cold end and the hot end of the gas turbine are the same, the included angle between the connecting line of the upper right fulcrum and the hot center point and the axis of the right hot end connecting rod is 90.22 degrees.
Preferably, the spherical hinge connection center of the right hot end connecting rod and the gas turbine is higher than the thermal center point.
Preferably, when the temperatures of the cold end and the hot end of the gas turbine are the same, the included angle between the connecting line of the upper right fulcrum and the hot center point and the axis of the right hot end connecting rod is 90.16 degrees.
Preferably, the spherical hinge connection center of the right hot end connecting rod and the gas turbine is lower than the thermal center point.
Preferably, when the temperatures of the cold end and the hot end of the gas turbine are the same, the included angle between the connecting line of the upper right fulcrum and the hot center point and the axis of the right hot end connecting rod is 90.29 degrees.
According to the gas turbine supporting structure, the left hot end connecting rod 21 and the right hot end connecting rod 22 of the hot end support 20 are symmetrically connected to the left side and the right side of the gas turbine 50, the left hot end connecting rod 21 and the right hot end connecting rod 22 are connected with the gas turbine 50 and the base 40 through spherical hinges, the weight of the hot end of the gas turbine 50 is supported, after the gas turbine 50 is heated and expanded in a working mode, the thermal center point in the hot end support plane is not deviated, and meanwhile the gas turbine 50 is allowed to freely expand axially and radially, so that the central axis of the whole gas turbine 50 is not deviated in an angular direction after heated and expanded, the problem of deviation of the thermal center point caused by radial expansion of the hot end of the gas turbine 50 can be effectively avoided, the coaxiality of an axial connecting piece is not influenced by the thermal expansion of the gas turbine 50, and the service life of an axial connecting piece and a bearing is prolonged.
Drawings
In order to more clearly illustrate the technical solutions of the present invention, the following brief description of the drawings is given for the purpose of the present invention, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and that other drawings can be obtained according to these drawings without the need for inventive work for a person skilled in the art.
FIG. 1 is a schematic general structural view of an embodiment of a gas turbine support structure of the present invention;
FIG. 2 is a hot end view of an embodiment of a gas turbine support structure of the present invention;
FIG. 3 is a hot end support schematic view of an embodiment of a gas turbine support structure of the present invention;
FIG. 4 is a cold end view of an embodiment of a gas turbine support structure of the present invention;
FIG. 5 is a hot end view of another embodiment of a gas turbine support structure of the present invention;
FIG. 6 is a hot end view of yet another embodiment of a gas turbine support structure of the present invention.
Reference numerals illustrate:
10 cold end support; 20 hot end support; a 40 base; 50 gas turbines; 11 left cold end connecting rod; 12 right cold end connecting rod; 21 left hot end connecting rod; 22 right hot end connecting rod; 23 transverse pull rods; 31 an oil return pipe; 32 oil return sleeves; a is that R An upper right fulcrum; b (B) R A lower right fulcrum.
Detailed Description
The following description of the embodiments of the present invention will be made more apparent and fully hereinafter with reference to the accompanying drawings, in which some, but not all embodiments of the invention are shown. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
Example 1
As shown in fig. 1, the gas turbine support structure includes a cold end support 10 and a hot end support 20;
the cold end support 10 is fixed on the base 40 and is used for supporting the cold end weight of the gas turbine 50;
the hot end support 20 is fixed on the base 40 and is used for supporting the hot end weight of the gas turbine 50;
as shown in fig. 2, the hot side support 20 includes a left hot side connecting rod 21 and a right hot side connecting rod 22;
the lower end of the right hot end connecting rod 22 adopts a spherical hinge connection base 40, the upper end adopts a spherical hinge to be connected to the right side of the gas turbine 50, and the spherical hinge connection center of the right hot end connecting rod 22 and the gas turbine 50 is used as an upper right fulcrum A R The method comprises the steps of carrying out a first treatment on the surface of the The spherical hinge connection center of the right hot end connecting rod 22 and the base 40 is used as a right lower pivot B R ；
The axes of the left hot end connecting rod 21 and the right hot end connecting rod 22 are in the same hot end supporting plane, and the left hot end connecting rod 21 and the right hot end connecting rod 22 are symmetrically distributed on the left side and the right side of the gas turbine 50;
when the temperature of the cold end and the hot end of the gas turbine are the same, the right upper supporting point A R The included angle delta between the connecting line of the concentric heating center point O and the axis of the right hot end connecting rod 22 is 90.01 degrees to 91.00 degrees;
the thermal center point O is the intersection of the gas turbine axis and the hot end support plane.
The spherical hinge is a space connecting hinge and consists of two parts, namely a ball and a ball shell. The hinge allows only relative rotation of the two parts about a common center of sphere, limiting their relative movement in three directions. The engineering background of the spherical hinge is a spherical bearing, a fixed spherical hinge support and the like.
The accurate calculation method of the included angle delta value is as follows, as shown in fig. 3, assuming that the radial unilateral expansion amount is a after the hot end of the gas turbine is heated and expanded, and assuming that the position of the upper right fulcrum is A after the hot end of the gas turbine is heated and expanded R Point change to A R ' Point, then A R ' Point and lower right fulcrum B R The following positional relationship needs to be satisfied: a is that R ' Point-on-line OA R On the extension line of (a) and connecting line A R A R ' length is equal to a, lower right fulcrum B R In connection line A R A R The right lower pivot point B is completely defined on the 'center vertical line' in combination with the relative height between the gas turbine 50 and the base 40 R Position, connection OA R And connecting line A R The included angle between B is delta. The distance between the cold end supporting plane and the hot end supporting plane is large, so that the center point offset caused by the axial expansion of the hot end of the gas turbine is negligible, if the axial expansion also needs to be considered for accurate calculation, the included angle delta can be adjusted to compensate the hot end center offset caused by the axial expansion of the hot end.
By accurately calculating the delta value of the included angle, the hot end of the gas turbine 50 can be ensured not to deviate from the hot center point in the hot end supporting plane after the hot end of the gas turbine 50 is expanded by working and heating, and meanwhile, the hot end of the gas turbine 50 is allowed to expand freely in the axial direction and the radial direction, so that the central axis of the whole gas turbine 50 is ensured not to deviate in the angular direction.
In the first embodiment of the gas turbine supporting structure, the left hot end connecting rod 21 and the right hot end connecting rod 22 of the hot end support 20 are symmetrically connected to the left side and the right side of the gas turbine 50, the left hot end connecting rod 21, the right hot end connecting rod 22, the gas turbine 50 and the base 40 are all connected by adopting spherical hinges, so that the weight of the hot end of the gas turbine 50 is supported, the thermal center point in the hot end supporting plane does not deviate after the gas turbine 50 is heated and expanded during working, and the gas turbine 50 is allowed to freely expand axially and radially, so that the central axis of the whole gas turbine 50 is ensured not to deviate in an angular direction after heated and expanded, the problem of deviation of the thermal center point caused by the radial expansion of the hot end of the gas turbine 50 can be effectively avoided besides the basic supporting effect, the coaxiality of an axial connecting piece is ensured not to be influenced by the thermal expansion of the gas turbine 50, and the service life of the axial connecting piece and the bearing is prolonged. The distance between the cold end support plane and the hot end support plane is generally large, so the center point offset caused by the axial expansion of the gas turbine 50 is negligible, if the axial expansion also needs to be considered for accurate calculation, the expansion amount a can be further finely adjusted to compensate the hot end center offset caused by the axial expansion.
Example two
The gas turbine support structure according to the first embodiment, the hot end support 20 further comprises a transverse pull rod 23;
the upper end of the transverse pull rod 23 is connected with the middle position of the bottom surface of the hot end of the gas turbine by adopting a spherical hinge, and the lower end of the transverse pull rod is connected with a base at the lower end of the right hot end connecting rod 22 or the left hot end connecting rod 21 by adopting a spherical hinge.
In the gas turbine support structure of the second embodiment, the transverse pull rod 23 is used for limiting the deflection of the hot end of the gas turbine in the left-right direction.
Example III
In the gas turbine support structure according to the first embodiment, as shown in fig. 4, the cold end support 10 includes a left cold end connecting rod 11 and a right cold end connecting rod 12;
the lower end of the right cold end connecting rod 12 is connected with the base 40 by adopting a spherical hinge, and the upper end is connected to the right side of the gas turbine 50 by adopting a spherical hinge;
the axes of the left cold end connecting rod 11 and the right cold end connecting rod 12 are in the same cold end supporting plane, and the left cold end connecting rod 11 and the right hot end connecting rod 12 are symmetrically distributed on the left side and the right side of the gas turbine 50.
In the gas turbine support structure of the third embodiment, the left cold end connecting rod 11 and the right cold end connecting rod 12 support the cold end weight of the gas turbine 50.
Example IV
The gas turbine support structure further comprises an oil return pipe 31 and an oil return sleeve 32, according to the first embodiment;
the oil return pipe 31 is fixed on an oil return port of a gearbox of the gas turbine 50;
the oil return sleeve 32 is fixed on an oil tank inlet of the base 40;
the oil return pipe 31 and the oil return sleeve 32 are round pipes, the outer diameter of the oil return pipe 31 is smaller than or equal to the inner diameter of the oil return sleeve 32, the oil return pipe 31 and the oil return sleeve 32 are connected in a cylindrical sleeve mode, and the oil return pipe 31 can axially slide or circumferentially rotate in the oil return sleeve 32;
the matching surface of the oil return pipe and the oil return sleeve is provided with an oil seal.
Preferably, the oil return pipe 31 is fixed on an oil return port of a gearbox of the gas turbine 50 through bolts; the oil return sleeve 32 is fixed on an oil inlet of the oil tank of the base 40 through bolts.
Preferably, the gearbox return port of the gas turbine 50 is located at the cold end of the gas turbine 50.
In the gas turbine supporting structure of the fourth embodiment, the sleeve assembly composed of the oil return pipe 31 and the oil return sleeve 32 can limit the lateral movement of the gas turbine 50, so that the gas turbine 50 can be adjusted at will in the height direction, and meanwhile, the sleeve assembly is used as a lubricating oil return pipe, and an oil seal is arranged on the matching surface of the oil return pipe and the oil return sleeve to prevent leakage of lubricating oil. In addition, because the sleeve assembly limits the gas turbine lateral displacement, the center point position of the gas turbine 50 axis in the cold end support plane is not shifted all the time, and the gas turbine thermal center point is not shifted, so the entire gas turbine axis is not angularly shifted.
Example five
Based on the gas turbine supporting structure of the first embodiment, the right hot end connecting rod 22 and the spherical hinge connection center of the gas turbine 50(upper right fulcrum A) R ) And the left hot end connecting rod 21 is as high as the hot center point O with the spherical hinge connection center (upper left fulcrum) of the gas turbine 50, as shown in fig. 2.
Preferably, when the temperature of the cold end and the hot end of the gas turbine are the same, the upper right fulcrum A R The angle delta between the line connecting the hot center point O and the axis of the right hot end link 22 is 90.22 deg..
Example six
Based on the gas turbine support structure of the first embodiment, the right hot end connecting rod 22 is connected with the spherical hinge center (upper right fulcrum a) of the gas turbine 50 R ) And the spherical hinge connection center (upper left fulcrum) of the left hot end connecting rod 21 and the gas turbine 50 is higher than the thermal center point O, as shown in fig. 5.
Preferably, when the temperature of the cold end and the hot end of the gas turbine are the same, the upper right fulcrum A R The angle delta between the line connecting the hot center point O and the axis of the right hot end link 22 is 90.16 deg..
Example seven
Based on the gas turbine support structure of the first embodiment, the right hot end connecting rod 22 is connected with the spherical hinge center (upper right fulcrum a) of the gas turbine 50 R ) And the spherical hinge connection center (upper left fulcrum) of the left hot-end connecting rod 21 and the gas turbine 50 is lower than the thermal center point O as shown in fig. 6.
Preferably, when the temperature of the cold end and the hot end of the gas turbine are the same, the upper right fulcrum A R The angle delta between the line connecting the hot center point O and the axis of the right hot end link 22 is 90.29 °.
The foregoing is merely a preferred embodiment of the present application and is not intended to limit the present application. Various modifications and changes may be made to the present application by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principles of the present application should be included in the protection scope of the present application.
Claims (11)
1. A gas turbine support structure comprising a cold end support and a hot end support;
the cold end support is fixed on the base and used for supporting the cold end weight of the gas turbine;
the hot end support is fixed on the base and used for supporting the weight of the hot end of the gas turbine;
the hot end support comprises a left hot end connecting rod and a right hot end connecting rod;
the lower end of the right hot end connecting rod is connected with the base by adopting a spherical hinge, the upper end of the right hot end connecting rod is connected to the right side of the gas turbine by adopting a spherical hinge, and the spherical hinge connecting center of the right hot end connecting rod and the gas turbine is used as an upper right fulcrum; the right hot end connecting rod is connected with the spherical hinge of the base to be used as a right lower fulcrum by the central meter;
the axes of the left hot end connecting rod and the right hot end connecting rod are in the same hot end supporting plane, and the left hot end connecting rod and the right hot end connecting rod are symmetrically distributed on the left side and the right side of the gas turbine;
when the temperatures of the cold end and the hot end of the gas turbine are the same, the included angle between the connecting line of the upper right fulcrum and the hot center point and the axis of the right hot end connecting rod is 90.01-91.00 degrees;
the thermal center point is the intersection point of the gas turbine axis and the hot end support plane.
2. The gas turbine support structure of claim 1,
the hot end support also comprises a transverse pull rod;
the upper end of the transverse pull rod is connected with the middle position of the bottom surface of the hot end of the gas turbine by adopting a spherical hinge, and the lower end of the transverse pull rod is connected with a base at the lower end of the right hot end connecting rod or the left hot end connecting rod by adopting a spherical hinge.
3. The gas turbine support structure of claim 1,
the cold end support comprises a left cold end connecting rod and a right cold end connecting rod;
the lower end of the right cold end connecting rod is connected with the base by adopting a spherical hinge, and the upper end of the right cold end connecting rod is connected to the right side of the gas turbine by adopting a spherical hinge;
the axes of the left cold end connecting rod and the right cold end connecting rod are in the same cold end supporting plane, and the left cold end connecting rod and the right cold end connecting rod are symmetrically distributed on the left side and the right side of the gas turbine.
4. The gas turbine support structure of claim 1,
the gas turbine support structure further comprises an oil return pipe and an oil return sleeve;
the oil return pipe is fixed on an oil return port of the gearbox of the gas turbine;
the oil return sleeve is fixed on an oil inlet of an oil tank of the base;
the oil return pipe and the oil return sleeve are round pipes, the outer diameter of the oil return pipe is smaller than or equal to the inner diameter of the oil return sleeve, the oil return pipe and the oil return sleeve are connected in a cylindrical sleeve mode, and the oil return pipe can axially slide or circumferentially rotate in the oil return sleeve;
the matching surface of the oil return pipe and the oil return sleeve is provided with an oil seal.
5. The gas turbine support structure of claim 4,
the oil return pipe is fixed on an oil return port of the gearbox of the gas turbine through a bolt;
the oil return sleeve is fixed on an oil inlet of the base oil tank through a bolt;
the oil return port of the gas turbine gearbox is positioned at the cold end of the gas turbine.
6. The gas turbine support structure of claim 1,
the right hot end connecting rod and the spherical hinge connecting center of the gas turbine are equal in height to the spherical hinge connecting center of the gas turbine.
7. The gas turbine support structure of claim 6,
when the temperatures of the cold end and the hot end of the gas turbine are the same, the included angle between the connecting line of the upper right fulcrum and the hot center point and the axis of the right hot end connecting rod is 90.22 degrees.
8. The gas turbine support structure of claim 1,
the spherical hinge connection center of the right hot end connecting rod and the gas turbine and the spherical hinge connection center of the left hot end connecting rod and the gas turbine are higher than the thermal center point.
9. The gas turbine support structure of claim 8,
when the temperatures of the cold end and the hot end of the gas turbine are the same, the included angle between the connecting line of the upper right fulcrum and the hot center point and the axis of the right hot end connecting rod is 90.16 degrees.
10. The gas turbine support structure of claim 1,
the spherical hinge connection center of the right hot end connecting rod and the gas turbine and the spherical hinge connection center of the left hot end connecting rod and the gas turbine are lower than the thermal center point.
11. The gas turbine support structure of claim 1,
when the temperatures of the cold end and the hot end of the gas turbine are the same, the included angle between the connecting line of the upper right fulcrum and the hot center point and the axis of the right hot end connecting rod is 90.29 degrees.
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| CN112523871B (en) * | 2020-11-30 | 2021-12-17 | 航发燃机(株洲)有限公司 | Gas turbine supporting device |
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| Title |
|---|
| 舰船燃气轮机支撑系统结构设计及抗冲击计算分析;尹家录等;航空发动机;第37卷(第03期);第12-14、33页 * |
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| Publication number | Publication date |
|---|---|
| CN108708789A (en) | 2018-10-26 |
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