CN105626269A - Supporting device of gas turbine - Google Patents
Supporting device of gas turbine Download PDFInfo
- Publication number
- CN105626269A CN105626269A CN201511008224.8A CN201511008224A CN105626269A CN 105626269 A CN105626269 A CN 105626269A CN 201511008224 A CN201511008224 A CN 201511008224A CN 105626269 A CN105626269 A CN 105626269A
- Authority
- CN
- China
- Prior art keywords
- internal combustion
- combustion turbine
- supplemental support
- main support
- seat
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Classifications
-
- 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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention relates to a supporting device of a gas turbine. The supporting device comprises an installation base, main supporting legs, main supporting adapter coupling supports, auxiliary supporting legs, auxiliary supporting bases and an anti-deflection device; the installation base is placed in a manner of being parallel to the ground, the upper face is an installation face, the lower face is a supporting face, and the supporting face of the installation base is in contact with the ground; one ends of the two main supporting legs are vertically installed on the installation face of the installation base and are fixedly connected with the installation face through bolts, the other ends of the main supporting legs are fixedly provided with the main supporting adapter coupling supports, and the two auxiliary supporting bases are further installed on the installation face of the installation base; the auxiliary supporting legs are installed on the auxiliary supporting bases and hinged to the auxiliary supporting bases through spherical hinges; and a rectangle is formed by the main supporting legs and the auxiliary supporting legs, and the anti-deflection device is arranged in the middle position of a connecting line of the two auxiliary supporting legs and fixedly connected with the installation base. By means of the supporting device of the gas turbine, the requirement for reliability can be met, the shock resistance is improved, and the supporting device has the beneficial effects of being simple in structure, easy and convenient to operate and the like.
Description
Technical field
The invention belongs to gas turbine technology field, particularly relate to a kind of internal combustion turbine bracing or strutting arrangement.
Background technology
Internal combustion turbine is taking the gas of continuous flow as working medium impeller high speed rotating, is the internal combustion type power machine of useful work by the energy conversion of fuel, is a kind of rotary vane type Thermal Motor. But internal combustion turbine not only needs to carry out body design, in addition it is also necessary to carry out supporting the design of device. In the design of internal combustion turbine support system, it is necessary to consider many-sided factor, such as reliability, economy and impact resistance etc. Industrial fuel gas wheel machine host by floor installation on stand, simultaneously by major-minor support leg by dynamic changes process to stand. In order to ensure the stress level that combustion engine is born and level of vibration in allowed limits, support system just needs to ensure the normal operation of combustion engine. If the intensity of combustion engine support system, rigidity are inadequate or unreasonable allocation, not only the normal operation of combustion engine can not be guaranteed, but also can destroy the stability that combustion engine holds Force system, the security of internal combustion turbine work is constituted a threat to.
Summary of the invention
It is an object of the invention to provide a kind of internal combustion turbine bracing or strutting arrangement, solve current internal combustion turbine and support device reliability and the low problem of impact resistance.
For achieving the above object, the technical solution used in the present invention is: a kind of internal combustion turbine bracing or strutting arrangement, comprises mounting seat, main support leg, main support Change-over frame, supplemental support leg, supplemental support seat and anti-deflection device;
Described mounting seat placement parallel to the ground and be mounting face above, bearing surface below, the bearing surface of mounting seat contacts with ground, one end of two described main support legs is vertically mounted on the mounting face of described mounting seat and is bolted to connection, the other end of described main support leg is installed with described main support Change-over frame, mounting face in described mounting seat is also equipped with two supplemental support seats, supplemental support seat is provided with supplemental support leg and hinged by ball, described main support leg and supplemental support leg form rectangular shape, it is provided with anti-deflection device in the line mid-way of two described supplemental support legs, described anti-deflection device is fixedly connected with described mounting seat.
Further, described main support Change-over frame comprises main support axle journal and the first spheroid ring, and described main support Change-over frame supports internal combustion turbine by main support axle journal and the first spheroid ring.
Further, described supplemental support leg comprises the 2nd spheroid ring and supplemental support axle journal, and described supplemental support leg supports internal combustion turbine by the 2nd spheroid ring and supplemental support axle journal.
Further, described anti-deflection device comprises anti-bias swinging rack, anti-bias pendulum location seat and jackscrew, described anti-bias swinging rack one end is installed on the Connection Block of anti-bias pendulum location seat, anti-bias swinging rack is fixed by the threaded hole that two jackscrews are provided with through described Connection Block, the axis collinear of two described jackscrews, the other end of anti-bias swinging rack is connected with internal combustion turbine, and the bottom of described anti-bias pendulum location seat is fixedly connected with described mounting seat.
Further, also comprise adjusting pad, it is installed between mounting seat and main support leg or between mounting seat and supplemental support seat, for adjusting main installation leg or the height of auxiliary installation leg.
Further, described supplemental support journal structure is Y font.
Further, described anti-bias swinging rack structure is Y font.
A kind of internal combustion turbine bracing or strutting arrangement of the present invention can meet reliability requirement and turn improve impact resistance, has the advantages such as structure is simple, easy and simple to handle.
Accompanying drawing explanation
Accompanying drawing herein is by being incorporated in specification sheets and forms the part of this specification sheets, shows embodiment according to the invention, and is used from the principle explaining the present invention with specification sheets one.
Fig. 1 is that the structural representation of device supported by internal combustion turbine according to an embodiment of the invention;
Fig. 2 is the connection structural representation of main according to an embodiment of the invention support Change-over frame and internal combustion turbine;
Fig. 3 is the connection structural representation assisted according to an embodiment of the invention and support leg and internal combustion turbine;
Fig. 4 is the connection structural representation of anti-deflection device and internal combustion turbine according to an embodiment of the invention;
Wherein, 1 is mounting seat, and 2 is main support leg, 3 is main support Change-over frame, and 4 is auxiliary support leg, and 5 is auxiliary support seat, 6 is anti-deflection device, and 7 is adjusting pad, and 8 is internal combustion turbine, 31 is main support axle journal, and 32 is the first spheroid ring, and 41 is the 2nd spheroid ring, 42 is supplemental support axle journal, and 61 is anti-bias swinging rack, and 62 is anti-bias pendulum location seat, 63 is jackscrew, and 621 is Connection Block.
Embodiment
For making object of the invention process, technical scheme and advantage clearly, below in conjunction with the accompanying drawing in the embodiment of the present invention, the technical scheme in the embodiment of the present invention is further described in more detail. In the accompanying drawings, same or similar label represents same or similar element or has element that is identical or similar functions from start to finish. Described embodiment is the present invention's part embodiment, instead of whole embodiments. It is exemplary type below by the embodiment being described with reference to the drawings, it is intended to for explaining the present invention, and limitation of the present invention can not be interpreted as. Based on the embodiment in the present invention, those of ordinary skill in the art, not making under creation type work prerequisite other embodiments all obtained, belong to the scope of protection of the invention. Below in conjunction with accompanying drawing, embodiments of the invention are described in detail.
In describing the invention, it will be appreciated that, term " " center ", " longitudinal direction ", " transverse direction ", " front ", " afterwards ", " left side ", " right side ", " vertically ", " level ", " top ", " end ", " interior ", it is based on orientation shown in the drawings or position relation that the orientation of the instruction such as " outward " or position are closed, it is only the present invention for convenience of description and simplified characterization, instead of indicate or imply that the device referred to or element must have specific orientation, with specific orientation structure and operation, therefore limiting the scope of the invention can not be interpreted as.
A kind of internal combustion turbine bracing or strutting arrangement being illustrated in figure 1 the present invention, comprises mounting seat 1, main support leg 2, main support Change-over frame 3, supplemental support leg 4, supplemental support seat 5 and anti-deflection device 6, mounting seat 1 placement parallel to the ground and be mounting face above, bearing surface below, the bearing surface of mounting seat 1 contacts with ground, one end of two main support legs 2 is vertically mounted on the mounting face of mounting seat 1 and is bolted to connection, the other end of main support leg 1 is installed with main support Change-over frame 3, mounting face in mounting seat 1 is also equipped with two supplemental support seats 5, supplemental support seat 5 is provided with supplemental support leg 4 and hinged by ball, main support leg 2 forms rectangular shape with supplemental support leg 4, it is provided with anti-deflection device 6 in the line mid-way of two supplemental support legs 4, anti-deflection device 6 is fixedly connected with mounting seat 1.
Concrete, according to the power stage mode of internal combustion turbine 8, main support big for rigidity being arranged on air inlet place near power take-off, supplemental support is arranged on exhaust place. The thermal stresses axially produced with radial thermal expansion when internal combustion turbine 8 works to reduce, supplemental support and main support acting in conjunction ensure that the reliable of internal combustion turbine 1 is fixed, moreover it is possible to adapt to axis when internal combustion turbine 8 works and radial thermal expansion.
It is noted that main support Change-over frame 3 comprises main support axle journal 31 and the first spheroid ring 32, main support Change-over frame 3 supports internal combustion turbine 8 by main support axle journal 31 and the first spheroid ring 32.
Concrete, as shown in Figure 2, main support is made up of two main support legs 2 and main support Change-over frame 3, assume responsibility for horizontal, axial and vertical load. Two main support legs 2 are distributed in the side, two, left and right of internal combustion turbine symmetrically. The tie point of main support and internal combustion turbine 8 is positioned on the horizontal central plane of the axis of internal combustion turbine 8, adopts bolt to be fixedly connected with, be rigidly fixed in mounting seat 1 between the following and mounting seat 1 of main support leg 2. In order to avoid assembly stress, main support Change-over frame 3 is connected with internal combustion turbine main frame 8 by the first spheroid ring 32, main support axle journal 31. Two grooves are had at internal combustion turbine 8 outer side. In the horizontal plane at the axis place being arranged in internal combustion turbine 8 of two groove symmetries, main support axle journal 31 gos deep in groove, is then fixedly connected with internal combustion turbine 8 by main support axle journal 31 with screw.
It is noted that supplemental support leg 4 comprises the 2nd spheroid ring 41 and supplemental support axle journal 42, supplemental support leg 4 supports internal combustion turbine 8 by the 2nd spheroid ring 41 and supplemental support axle journal 42.
It is to be noted, anti-deflection device 6 comprises anti-bias swinging rack 61, anti-bias pendulum location seat 62 and jackscrew 63, anti-bias swinging rack 61 one end is installed on the Connection Block 621 of anti-bias pendulum location seat 62, anti-bias swinging rack 62 is fixed by the threaded hole that two jackscrews 63 are provided with through Connection Block 621, the axis collinear of two jackscrews 63, the other end of anti-bias swinging rack 61 is connected with internal combustion turbine 8, and the bottom of anti-bias pendulum location seat 62 is fixedly connected with mounting seat 1.
Concrete, as shown in Figure 3 and Figure 4, supplemental support is made up of two supplemental support legs 4 and supplemental support seat 5, only undertakes vertical load. Similar with main support, two supplemental support legs 4 are same with supplemental support seat 5 is distributed in the internal combustion turbine left and right sides symmetrically. On supplemental support leg 4 horizontal central plane being positioned at internal combustion turbine 8 same with the tie point of internal combustion turbine 8, the difference is that supplemental support by the 2nd spheroid ring 41 and realizes sphere between supplemental support axle journal 42 with internal combustion turbine 8 and the conical surface is connected, axis and the radial thermal expansion of internal combustion turbine 8 can be absorbed, the luffing angle of internal combustion turbine 8 can be controlled again. Supplemental support leg 4 is connected with supplemental support seat 5 by globular hinge. Owing to the upper and lower ends of supplemental support is by globular hinge anatomical connectivity, not can the horizontal degree of freedom of restricting host, be therefore provided with anti-deflection device 6 in the underface in internal combustion turbine supplemental support cross section. Anti-deflection device 6 utilizes two jackscrews 63 only to limit the transverse impact of internal combustion turbine 8, axis and vertical freedom degree is not limited.
It is noted that also comprise adjusting pad 7, it is installed between mounting seat 1 and main support leg 2 or between mounting seat 1 and supplemental support seat 5, for adjusting the height of main installation leg 2 or auxiliary installation leg 4.
Concrete, when adjusting height or the output shaft centering of internal combustion turbine axis, it is possible to regulate the adjusting pad 7 below main support or supplemental support, thus reach the height of adjustment internal combustion turbine 8 and the object of luffing angle.
It is noted that supplemental support axle journal 42 structure is Y font; It is noted that anti-bias swinging rack 61 structure is Y font. As shown in Figure 1, one end of the main support leg 2 of internal combustion turbine 8 is the inlet mouth of internal combustion turbine 8, one end of the supplemental support leg 4 of internal combustion turbine 8 is outlet side, as shown in Figure 3 and Figure 4, (namely project on vertical plane) in terms of direction, air outlet from the inlet mouth of internal combustion turbine, auxiliary support axle journal 42 and anti-bias swinging rack are all the structures of Y type, adopt Y font structure that the internal combustion turbine of auxiliary support axle journal 42 or anti-bias swinging rack 61 support cylinder shape can be made more firm.
The internal combustion turbine bracing or strutting arrangement of the present invention can meet reliability requirement and turn improve impact resistance, has the advantages such as structure is simple, the lifting settling time is short, easy and simple to handle.
The above; the optimum embodiment being only the present invention, but protection scope of the present invention is not limited thereto, any is familiar with those skilled in the art in the technical scope that the present invention discloses; the change that can expect easily or replacement, all should be encompassed within protection scope of the present invention. Therefore, protection scope of the present invention should be as the criterion with the protection domain of described claim.
Claims (7)
1. an internal combustion turbine bracing or strutting arrangement, it is characterized in that, comprise mounting seat (1), main support leg (2), main support Change-over frame (3), supplemental support leg (4), supplemental support seat (5) and anti-deflection device (6);
Described mounting seat (1) placement parallel to the ground and be mounting face above, bearing surface below, the bearing surface of mounting seat (1) contacts with ground, one end of two described main support legs (2) is vertically mounted on the mounting face of described mounting seat (1) and is bolted to connection, the other end of described main support leg (1) is installed with described main support Change-over frame (3), mounting face in described mounting seat (1) is also equipped with two supplemental support seats (5), supplemental support seat (5) is provided with supplemental support leg (4) and hinged by ball, described main support leg (2) forms rectangular shape with supplemental support leg (4), it is provided with anti-deflection device (6) in the line mid-way of two described supplemental support legs (4), described anti-deflection device (6) is fixedly connected with described mounting seat (1).
2. internal combustion turbine bracing or strutting arrangement according to claim 1, it is characterized in that, described main support Change-over frame (3) comprises main support axle journal (31) and the first spheroid ring (32), and described main support Change-over frame (3) supports internal combustion turbine (8) by main support axle journal (31) and the first spheroid ring (32).
3. internal combustion turbine bracing or strutting arrangement according to claim 1, it is characterized in that, described supplemental support leg (4) comprises the 2nd spheroid ring (41) and supplemental support axle journal (42), and described supplemental support leg (4) supports internal combustion turbine (8) by the 2nd spheroid ring (41) and supplemental support axle journal (42).
4. internal combustion turbine bracing or strutting arrangement according to claim 1, it is characterized in that, described anti-deflection device (6) comprises anti-bias swinging rack (61), anti-bias pendulum location seat (62) and jackscrew (63), described anti-bias swinging rack (61) one end is installed on the Connection Block (621) of anti-bias pendulum location seat (62), anti-bias swinging rack (62) is fixed by the threaded hole that two jackscrews (63) are provided with through described Connection Block (621), the axis collinear of two described jackscrews (63), the other end of anti-bias swinging rack (61) is connected with internal combustion turbine (8), the bottom of described anti-bias pendulum location seat (62) is fixedly connected with described mounting seat (1).
5. internal combustion turbine bracing or strutting arrangement according to claim 1, it is characterized in that, described internal combustion turbine bracing or strutting arrangement also comprises adjusting pad (7), it is installed between mounting seat (1) and main support leg (2) or between mounting seat (1) and supplemental support seat (5), for adjusting main installation leg (2) or the height of auxiliary installation leg (4).
6. internal combustion turbine bracing or strutting arrangement according to claim 3, it is characterised in that, described supplemental support axle journal (42) structure is Y font.
7. internal combustion turbine bracing or strutting arrangement according to claim 4, it is characterised in that, described anti-bias swinging rack (61) structure is Y font.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201511008224.8A CN105626269A (en) | 2015-12-29 | 2015-12-29 | Supporting device of gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201511008224.8A CN105626269A (en) | 2015-12-29 | 2015-12-29 | Supporting device of gas turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105626269A true CN105626269A (en) | 2016-06-01 |
Family
ID=56041540
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201511008224.8A Pending CN105626269A (en) | 2015-12-29 | 2015-12-29 | Supporting device of gas turbine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105626269A (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106289785A (en) * | 2016-08-26 | 2017-01-04 | 中科合肥微小型燃气轮机研究院有限责任公司 | Gas turbine positioning supporting frame |
| CN106769063A (en) * | 2016-12-21 | 2017-05-31 | 中国燃气涡轮研究院 | A kind of integrative installation technology frame for aeroengine test run |
| CN108708789A (en) * | 2018-08-15 | 2018-10-26 | 上海和兰透平动力技术有限公司 | Gas turbine support construction |
| CN109184920A (en) * | 2018-08-27 | 2019-01-11 | 中国航发沈阳发动机研究所 | A kind of axial direction anti whip device |
| RU2678187C2 (en) * | 2017-06-16 | 2019-01-24 | Публичное акционерное общество "ОДК-Уфимское моторостроительное производственное объединение" (ПАО "ОДК-УМПО") | Mounting bracket of unit on shell of turbomachine body |
| CN110226027A (en) * | 2017-01-26 | 2019-09-10 | 通用电气公司 | System and method for installing rotatable machine |
| CN112523871A (en) * | 2020-11-30 | 2021-03-19 | 航发燃机(株洲)有限公司 | Gas turbine supporting device |
| CN113586245A (en) * | 2021-08-31 | 2021-11-02 | 中国联合重型燃气轮机技术有限公司 | Gas turbine's strutting arrangement and gas turbine |
-
2015
- 2015-12-29 CN CN201511008224.8A patent/CN105626269A/en active Pending
Non-Patent Citations (1)
| Title |
|---|
| 尹家录等: "舰船燃气轮机支撑***结构设计及抗冲击计算分析", 《航空发动机》 * |
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106289785A (en) * | 2016-08-26 | 2017-01-04 | 中科合肥微小型燃气轮机研究院有限责任公司 | Gas turbine positioning supporting frame |
| CN106289785B (en) * | 2016-08-26 | 2019-04-30 | 中科合肥微小型燃气轮机研究院有限责任公司 | Gas turbine positioning supporting frame |
| CN106769063A (en) * | 2016-12-21 | 2017-05-31 | 中国燃气涡轮研究院 | A kind of integrative installation technology frame for aeroengine test run |
| CN110226027A (en) * | 2017-01-26 | 2019-09-10 | 通用电气公司 | System and method for installing rotatable machine |
| RU2678187C2 (en) * | 2017-06-16 | 2019-01-24 | Публичное акционерное общество "ОДК-Уфимское моторостроительное производственное объединение" (ПАО "ОДК-УМПО") | Mounting bracket of unit on shell of turbomachine body |
| CN108708789A (en) * | 2018-08-15 | 2018-10-26 | 上海和兰透平动力技术有限公司 | Gas turbine support construction |
| CN108708789B (en) * | 2018-08-15 | 2024-03-15 | 上海和兰透平动力技术有限公司 | Gas turbine support structure |
| CN109184920A (en) * | 2018-08-27 | 2019-01-11 | 中国航发沈阳发动机研究所 | A kind of axial direction anti whip device |
| CN112523871A (en) * | 2020-11-30 | 2021-03-19 | 航发燃机(株洲)有限公司 | Gas turbine supporting device |
| CN112523871B (en) * | 2020-11-30 | 2021-12-17 | 航发燃机(株洲)有限公司 | Gas turbine supporting device |
| CN113586245A (en) * | 2021-08-31 | 2021-11-02 | 中国联合重型燃气轮机技术有限公司 | Gas turbine's strutting arrangement and gas turbine |
| CN113586245B (en) * | 2021-08-31 | 2022-04-26 | 中国联合重型燃气轮机技术有限公司 | Gas turbine's strutting arrangement and gas turbine |
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Application publication date: 20160601 |
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