CN209743039U - Fixing device of high-frequency acceleration sensor of gas turbine - Google Patents
Fixing device of high-frequency acceleration sensor of gas turbine Download PDFInfo
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- CN209743039U CN209743039U CN201920101507.4U CN201920101507U CN209743039U CN 209743039 U CN209743039 U CN 209743039U CN 201920101507 U CN201920101507 U CN 201920101507U CN 209743039 U CN209743039 U CN 209743039U
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Abstract
the utility model discloses a gas turbine high frequency acceleration sensor's fixing device belongs to gas turbine on-line monitoring, failure diagnosis and discernment technical field. The fixing device comprises a first support (1), a second support (2), a third support (3) and a fourth support (4), wherein the first support (1) and the second support (2) are arranged on a flange face (5) of a front flange of the gas turbine, the third support (3) is arranged on a flange face (6) of a middle flange of the gas turbine, and the fourth support (4) is arranged on a flange face (7) of a rear flange of the gas turbine; the natural frequencies of the first support (1), the second support (2), the third support (3) and the fourth support (4) are all larger than 1000Hz, and the first support (1), the second support (2), the third support (3) and the fourth support (4) are provided with high-frequency acceleration sensors in a one-to-one correspondence mode. The fixing device realizes the installation and the fixation of the high-frequency acceleration sensor in the gas turbine.
Description
Technical Field
The utility model relates to a gas turbine on-line monitoring, failure diagnosis and discernment technical field, in particular to gas turbine high frequency acceleration sensor's fixing device.
Background
The gas turbine is used as a main power device in a natural gas transportation project, the normal operation of the gas turbine depends on reliable real-time state monitoring and fault diagnosis, and the state monitoring based on vibration is the core part of the state monitoring of the gas turbine, so that how to accurately acquire the vibration signal of the gas turbine is very important.
in the related art, a vibration sensor is mounted in a structure of a gas turbine itself, and the vibration sensor is disposed on a flange surface of the gas turbine through a mounting bracket to acquire information of amplitude, frequency, phase, and the like of a machine body, a rotor, or other parts.
However, since the fault signal of the gas turbine is transmitted to the casing from the inside, the fault signal has the characteristics of high frequency, complex transmission path, weak fault characteristics and the like, and the vibration sensor in the related art does not have the capability of acquiring the high-frequency vibration signal, so that the acquired information of the amplitude, the frequency, the phase and the like of the engine body, the rotor or other parts is not accurate enough; meanwhile, even if a high-frequency acceleration sensor is installed on the existing installation support, the existing installation support is easy to resonate with a gas turbine in the working process, and information such as amplitude, frequency and phase of a machine body, a rotor or other parts is difficult to acquire.
SUMMERY OF THE UTILITY MODEL
In view of this, the utility model provides a gas turbine high frequency acceleration sensor's fixing device has realized the installation of high frequency acceleration sensor in gas turbine and has fixed, is convenient for to the collection of gas turbine high frequency vibration signal.
Specifically, the method comprises the following technical scheme:
a gas turbine high frequency acceleration sensor fixture, the fixture comprising: a first bracket, a second bracket, a third bracket and a fourth bracket, wherein,
The first support and the second support are arranged on the flange surface of a front flange of the gas turbine, the third support is arranged on the flange surface of a middle flange of the gas turbine, and the fourth support is arranged on the flange surface of a rear flange of the gas turbine;
The natural frequencies of the first support, the second support, the third support and the fourth support are all larger than 1000Hz, and high-frequency acceleration sensors are arranged on the first support, the second support, the third support and the fourth support in a one-to-one correspondence mode.
in one possible design, the first bracket comprises a first connecting piece and a first fixed seat which are connected;
the first connecting piece is provided with at least two first through holes, and one first through hole is used for being opposite to a screw hole on the flange surface of one front flange;
A first threaded hole is formed in the first fixing seat, and a screw rod on the high-frequency acceleration sensor is suitable for being inserted into the first threaded hole.
In one possible design, the first bracket further includes a first reinforcing rib;
The first reinforcing rib is arranged on the first fixing seat and connected with one side of the first connecting piece.
in one possible design, the second bracket comprises a second connecting piece and a second fixed seat which are connected;
The second connecting piece is provided with at least two second through holes, and one second through hole is used for being opposite to a screw hole on the flange surface of one front flange;
And a second threaded hole is formed in the second fixing seat, and a screw rod on the high-frequency acceleration sensor is suitable for being inserted into the second threaded hole.
In one possible embodiment, the second connecting element and the second fastening seat are integrally formed.
in one possible design, the third bracket comprises a third connecting piece and a third fixed seat which are connected;
the third connecting piece is provided with at least two third through holes, and one third through hole is used for being opposite to a screw hole on the flange surface of one middle flange;
And a third threaded hole is formed in the third fixing seat, and a screw rod on the high-frequency acceleration sensor is suitable for being inserted into the third threaded hole.
In one possible design, the third bracket further includes a second reinforcing rib;
The second reinforcing rib is arranged on the third fixing seat and connected with one side of the third connecting piece.
In one possible design, the fourth bracket comprises a fourth connecting piece and a fourth fixed seat which are connected;
the fourth connecting piece is provided with at least two fourth through holes, and one fourth through hole is used for being opposite to a screw hole on the flange surface of one rear flange;
and a fourth threaded hole is formed in the fourth fixing seat, and a screw rod on the high-frequency acceleration sensor is suitable for being inserted into the fourth threaded hole.
In one possible design, the fourth bracket further includes a third reinforcing rib;
the third reinforcing rib is arranged on the fourth fixing seat and connected with one side of the fourth connecting piece.
in one possible design, the fixing device further comprises: a plurality of bolts;
the plurality of bolts are adapted to mate with the first bracket, the second bracket, the third bracket, and the fourth bracket.
The embodiment of the utility model provides a technical scheme's beneficial effect includes at least:
The first bracket and the second bracket are arranged on the flange surface of the front flange of the gas turbine, the third bracket is arranged on the flange surface of the flange in the gas turbine, the fourth bracket is arranged on the flange surface of the rear flange of the gas turbine, and the high-frequency acceleration sensors are correspondingly arranged on the first bracket, the second bracket, the third bracket and the fourth bracket one by one to realize the installation and fixation of the high-frequency acceleration sensors in the gas turbine, because the natural frequencies of the first bracket, the second bracket, the third bracket and the fourth bracket are all larger than 1000Hz and are all larger than the maximum excitation frequency of the gas turbine in the working process, the resonance between the first support or the second support or the third support or the fourth support and the gas turbine in the working process can be effectively avoided, so that the high-frequency acceleration sensor can acquire the high-frequency vibration signals of the gas turbine.
Drawings
In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings needed to be used in the description of the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings without creative efforts.
Fig. 1 is a schematic structural diagram of a fixing device of a high-frequency acceleration sensor of a gas turbine according to an embodiment of the present invention;
Fig. 2 is a front view of a first bracket in a fixing device of a high-frequency acceleration sensor of a gas turbine according to an embodiment of the present invention;
fig. 3 is a partial sectional side view of a first bracket of a fixing device for a high-frequency acceleration sensor of a gas turbine according to an embodiment of the present invention;
FIG. 4 is a top view taken along line A1-A1 of FIG. 2;
Fig. 5 is a front view of a second bracket in a fixing device of a high-frequency acceleration sensor of a gas turbine according to an embodiment of the present invention;
fig. 6 is a partial sectional side view of a second bracket in a fixing device of a high-frequency acceleration sensor of a gas turbine according to an embodiment of the present invention;
FIG. 7 is a top view taken along line A2-A2 of FIG. 5;
Fig. 8 is a front view of a third bracket in a fixing device of a high-frequency acceleration sensor of a gas turbine according to an embodiment of the present invention;
fig. 9 is a partial sectional side view of a third bracket in a fixing device for a high-frequency acceleration sensor of a gas turbine according to an embodiment of the present invention;
FIG. 10 is a top view taken along line A3-A3 of FIG. 8;
Fig. 11 is a front view of a fourth bracket in a fixing device of a high-frequency acceleration sensor of a gas turbine according to an embodiment of the present invention;
Fig. 12 is a partial sectional side view of a fourth bracket of a fixing device for a high-frequency acceleration sensor of a gas turbine according to an embodiment of the present invention;
FIG. 13 is a top view taken along line A4-A4 of FIG. 11.
the reference numerals in the drawings denote:
1-a first bracket, 11-a first connecting piece, 111-a first through hole, 12-a first fixed seat, 121-a first threaded hole, 13-a first reinforcing rib,
2-a second bracket, 21-a second connecting piece, 211-a second through hole, 22-a second fixed seat, 221-a second threaded hole,
3-a third bracket, 31-a third connecting piece, 311-a third through hole, 32-a third fixed seat, 321-a third threaded hole, 33-a second reinforcing rib,
4-a fourth bracket, 41-a fourth connecting piece, 411-a fourth through hole, 42-a fourth fixed seat, 421-a fourth threaded hole, 43-a third reinforcing rib,
5-the flange face of the front flange of the gas turbine,
6-flange face of flange in gas turbine,
7-flange face of gas turbine rear flange.
Detailed Description
Unless defined otherwise, all technical terms used in the embodiments of the present invention have the same meaning as commonly understood by one of ordinary skill in the art. Before further detailed description of embodiments of the present invention, definitions are given for understanding some terms of embodiments of the present invention.
In the embodiment of the present invention, the related "high frequency acceleration sensor" is a sensor capable of collecting high frequency vibration signals.
the high-frequency acceleration sensor can be used for acquiring high-frequency, high-speed and weak signals of high-frequency vibration signals transmitted to the outer casing from the inside of the unit. Through a vibration signal acquired by a high-frequency acceleration sensor and a subsequent signal processing method, an optimal characteristic extraction method suitable for a vibration signal of a gas turbine casing is researched, and the following mechanical faults can be analyzed, diagnosed, early-warned and alarmed: firstly, a blade fault: blade damage, ablation, breakage, etc.; bearing class failure: bearing spalling, wear, running sleeves, and the like; ③ rotor fault: the compressor and the turbine rotor are unbalanced, not centered, bent and the like.
in order to make the technical solutions and advantages of the present invention clearer, the following will describe the embodiments of the present invention in further detail with reference to the accompanying drawings.
the embodiment of the utility model provides a gas turbine high frequency acceleration sensor's fixing device, its schematic structure is shown in FIG. 1, and this fixing device includes: a first bracket 1, a second bracket 2, a third bracket 3 and a fourth bracket 4.
the first bracket 1 and the second bracket 2 are arranged on a flange surface 5 of a front flange of the gas turbine, the third bracket 3 is arranged on a flange surface 6 of a middle flange of the gas turbine, and the fourth bracket 4 is arranged on a flange surface 7 of a rear flange of the gas turbine;
The natural frequency of the first support 1, the second support 2, the third support 3 and the fourth support 4 is greater than 1000Hz, and the first support 1, the second support 2, the third support 3 and the fourth support 4 are provided with high-frequency acceleration sensors (not shown in the figure) in a one-to-one correspondence manner.
The maximum excitation frequency of the gas turbine during operation is 9000Hz, and by setting the natural frequencies of the first support 1, the second support 2, the third support 3 and the fourth support 4 to be greater than 1000Hz, resonance between the first support 1, the second support 2, the third support 3 or the fourth support 4 and the gas turbine during operation can be effectively avoided, and the resonance is prevented from influencing the measurement of the high-frequency signals by the high-frequency acceleration sensor.
the utility model discloses gas turbine high frequency acceleration sensor's fixing device's theory of operation does:
The installation and fixation of the high-frequency acceleration sensor in the gas turbine are realized by arranging the first bracket 1 and the second bracket 2 on the flange surface 5 of the front flange of the gas turbine, arranging the third bracket 3 on the flange surface 6 of the middle flange of the gas turbine and arranging the fourth bracket 4 on the flange surface 7 of the rear flange of the gas turbine, and by utilizing the high-frequency acceleration sensors which are correspondingly arranged on the first bracket 1, the second bracket 2, the third bracket 3 and the fourth bracket 4 one by one;
because the natural frequencies of the first support 1, the second support 2, the third support 3 and the fourth support 4 are all greater than 1000Hz and are all greater than the maximum excitation frequency of the gas turbine in the working process, the resonance between the first support 1 or the second support 2 or the third support 3 or the fourth support 4 and the gas turbine in the working process can be effectively avoided, and the high-frequency acceleration sensor can realize the acquisition of high-frequency vibration signals of the gas turbine.
therefore, the utility model discloses gas turbine high frequency acceleration sensor's fixing device utilizes first support 1, second support 2, third support 3 and fourth support 4, the installation and the fixing of high frequency acceleration sensor in gas turbine have been realized, be convenient for to gas turbine high frequency vibration signal's collection, in order to strengthen gas turbine running state's monitoring, auxiliary assembly operation management and maintenance person in time take the pertinence measure, reduce the risk that gas turbine takes place serious fault, reduce because of the economic loss that gas turbine parks and examines the maintenance and produce, do not influence gas turbine original equipment vibration sensor's installation simultaneously and can not need not attack the screw hole at the quick-witted casket surface, the integrality of outer quick-witted casket structure has been guaranteed.
The following further describes the fixing device of the high frequency acceleration sensor of the gas turbine according to the embodiment of the present invention:
the first bracket 1 is arranged on the flange surface 5 of the front flange of the gas turbine as shown in fig. 2 in a front view, fig. 3 in a partially sectional side view, and fig. 4 in a top view taken along line a1-a1 in fig. 2.
the first carrier 1 can be arranged radially on the flange surface 5 of the gas turbine front flange.
For example, one first bracket 1 may be installed in each of the horizontal direction and the vertical direction along the radial direction of the flange face 5 of the gas turbine front flange.
optionally, the first bracket 1 includes a first connecting member 11 and a first fixing seat 12 connected to each other, as shown in fig. 2, 3 or 4.
At least two first through holes 111 are formed in the first connecting member 11, as shown in fig. 2, one first through hole 111 is used for being opposite to a screw hole on the flange surface 5 of one front flange;
the first fixing seat 12 is provided with a first threaded hole 121, as shown in fig. 2, a screw rod on the high-frequency acceleration sensor is suitable for being inserted into the first threaded hole 121.
It can be understood that, because the flange face 5 of the front flange is circular in shape, and the distance between two adjacent screw holes is large, when the installation is convenient, the screw hole on the flange face 5 of one first through hole 111 and one front flange is opposite, the connection face between two adjacent first through holes 111 is an arc face, and the circle center corresponding to the arc face coincides with the hole center of the flange hole, as shown in fig. 2, the hole center distance between two adjacent first through holes 111 may be 36 mm.
The cross section of the first fixing seat 12 may be a cube, and as shown in fig. 4, the side length of the cross section may be 25 mm.
further, the first bracket 1 further includes a first reinforcing rib 13, and the first reinforcing rib 13 is disposed on the first fixing seat 12 and connected to one side of the first connecting member 11, as shown in fig. 3.
the first reinforcing ribs 13 are provided to enhance the structural rigidity of the first bracket 1.
The second bracket 2 is provided on the flange surface 5 of the front flange of the gas turbine as shown in fig. 5 in a front view, fig. 6 in a partially sectional side view, and fig. 7 in a top view taken along line a2-a2 in fig. 5.
the second carrier 2 can be arranged axially on the flange surface 5 of the gas turbine front flange.
Optionally, the second bracket 2 includes a second connecting member 21 and a second fixing seat 22 connected to each other, as shown in fig. 5, 6 or 7.
the second connecting member 21 is provided with at least two second through holes 211, as shown in fig. 5, one second through hole 211 is used for being opposite to a screw hole on the flange surface 5 of one front flange;
the second fixing seat 22 is provided with a second threaded hole 221, as shown in fig. 5 or fig. 6, the screw rod on the high-frequency acceleration sensor is suitable for being inserted into the second threaded hole 221.
it can be understood that, because the flange face 5 of the front flange is circular in shape, and the distance between two adjacent screw holes is large, when the mounting is convenient, two second through holes 211 are opposite to the screw holes on the flange face 5 of one front flange, the connection face between two adjacent second through holes 211 is an arc face, and the circle center corresponding to the arc face coincides with the hole center of the flange hole, as shown in fig. 5, the hole center distance between two adjacent second through holes 211 may be 36 mm.
the cross section of the second fixing seat 22 may be a rectangular parallelepiped, and as shown in fig. 7, the width of the cross section may be 6mm, and the length may be 25 mm.
Further, the second connecting member 21 and the second fixing seat 22 may be integrally formed, so as to facilitate manufacturing.
the third bracket 3 is provided on the flange surface 6 of the flange in the gas turbine, as shown in fig. 8 in a front view, fig. 9 in a partially sectional side view, and fig. 10 in a top view taken along line A3-A3 in fig. 8.
Optionally, the third bracket 3 includes a third connecting member 31 and a third fixing seat 32 connected to each other, as shown in fig. 8, 9 or 10.
At least two third through holes 311 are formed in the third connecting member 31, as shown in fig. 8, one third through hole 311 is used for being opposite to a screw hole on the flange surface 6 of one middle flange;
The third fixing seat 32 is provided with a third threaded hole 321, as shown in fig. 8 or fig. 9, the screw rod of the high-frequency acceleration sensor is adapted to be inserted into the third threaded hole 321.
The cross section of the third fixing seat 32 may be a cube, and as shown in fig. 10, the side length of the cross section may be 15 mm.
further, the third bracket 3 further includes a second reinforcing rib 33, and the second reinforcing rib 33 is disposed on the third fixing seat 32 and connected to one side of the third connecting member 31, as shown in fig. 9.
The second reinforcing ribs 33 are provided to enhance the structural rigidity of the third bracket 3.
The fourth bracket 4 is provided on the flange surface 7 of the gas turbine rear flange in a front view as shown in fig. 11, a partially sectional side view as shown in fig. 12, and a top view taken along a line a4-a4 in fig. 11 as shown in fig. 13.
optionally, the fourth bracket 4 includes a fourth connecting element 41 and a fourth fixing seat 42 connected to each other, as shown in fig. 11, 12 or 13.
At least two fourth through holes 411 are formed in the fourth connecting member 41, as shown in fig. 11, one fourth through hole 411 is used for being opposite to a screw hole on the flange surface 7 of one rear flange;
the fourth fixing seat 42 is provided with a fourth threaded hole 421, and as shown in fig. 11, a screw rod on the high-frequency acceleration sensor is adapted to be inserted into the fourth threaded hole 421.
The cross section of the fourth fixing seat 42 may be a cube, and as shown in fig. 13, the side length of the cross section may be 15 mm.
Further, the fourth bracket 4 further includes a third reinforcing rib 43, and the third reinforcing rib 43 is disposed on the fourth fixing seat 42 and connected to one side of the fourth connecting member 41, as shown in fig. 12.
The third reinforcing ribs 43 are provided to enhance the structural rigidity of the fourth bracket 4.
it is understood that the number of the first bracket 1, the second bracket 2, the third bracket 3 and the fourth bracket 4 may be one or more, and is not limited in particular.
based on the structure, the materials of the first bracket 1, the second bracket 2, the third bracket 3 and the fourth bracket 4 can be selected from 321 stainless steel, so that the first bracket, the second bracket, the third bracket and the fourth bracket are prevented from rusting and being difficult to disassemble in the using process.
further, for the convenience of the utility model discloses gas turbine high frequency acceleration sensor's fixing device's installation is fixed, and this fixing device still includes: a plurality of bolts (not shown in the figures).
A plurality of bolts are adapted to cooperate with the first bracket 1, the second bracket 2, the third bracket 3 and the fourth bracket 4. For example, when the first bracket 1 is installed, each first through hole 111 is opposite to a screw hole on the flange face 5 of one front flange, and a bolt is used to pass through each first through hole 111 and the screw hole on the flange face 5 of the opposite front flange, so that the first bracket 1 and the flange face 5 of the front flange are fixed by screwing.
in the embodiment of the present invention, taking the first bracket 1, the second bracket 2, the third bracket 3, and the fourth bracket 4 used in the model LM2500 of the gas turbine as an example, the natural frequency is measured, as shown in table 1 below:
TABLE 1 summary of the natural frequencies of the various stents
In a possible example, the operating personnel can take the fixing device of the gas turbine high frequency acceleration sensor and a plurality of high frequency acceleration sensors of the embodiment of the invention to the construction site, install the high frequency acceleration sensor on the first support 1, the second support 2, the third support 3 and the fourth support 4 in a one-to-one manner, reuse the bolt to fix the first support 1 and the second support 2 on the flange face 5 of the gas turbine front flange, fix the third support 3 on the flange face 6 of the gas turbine middle flange, fix the fourth support 4 on the flange face 7 of the gas turbine rear flange, so as to complete the installation of the fixing device.
in the present application, the terms "first" and "second" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance. The term "plurality" means two or more unless expressly limited otherwise.
The above description is only for facilitating the understanding of the technical solutions of the present invention by those skilled in the art, and is not intended to limit the present invention. 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 (10)
1. A fixing device for a high-frequency acceleration sensor of a gas turbine, characterized in that it comprises: a first bracket (1), a second bracket (2), a third bracket (3) and a fourth bracket (4), wherein,
the first bracket (1) and the second bracket (2) are arranged on a flange face (5) of a front flange of the gas turbine, the third bracket (3) is arranged on a flange face (6) of a flange in the gas turbine, and the fourth bracket (4) is arranged on a flange face (7) of a rear flange of the gas turbine;
The natural frequencies of the first support (1), the second support (2), the third support (3) and the fourth support (4) are all larger than 1000Hz, and high-frequency acceleration sensors are arranged on the first support (1), the second support (2), the third support (3) and the fourth support (4) in a one-to-one correspondence mode.
2. the fixing device of the high-frequency acceleration sensor of the gas turbine according to claim 1, characterized in that, the first bracket (1) comprises a first connecting piece (11) and a first fixed seat (12) which are connected;
At least two first through holes (111) are formed in the first connecting piece (11), and one first through hole (111) is used for being opposite to a screw hole in the flange face (5) of one front flange;
A first threaded hole (121) is formed in the first fixing seat (12), and a screw rod on the high-frequency acceleration sensor is suitable for being inserted into the first threaded hole (121).
3. the fixing device of a high-frequency acceleration sensor of a gas turbine according to claim 2, characterized in that said first bracket (1) further comprises a first reinforcement rib (13);
the first reinforcing rib (13) is arranged on the first fixed seat (12) and connected with one side of the first connecting piece (11).
4. The fixing device of the high-frequency acceleration sensor of the gas turbine according to claim 1, characterized in that, the second bracket (2) comprises a second connecting piece (21) and a second fixed seat (22) which are connected;
at least two second through holes (211) are formed in the second connecting piece (21), and one second through hole (211) is used for being opposite to a screw hole in the flange surface (5) of one front flange;
And a second threaded hole (221) is formed in the second fixed seat (22), and a screw rod on the high-frequency acceleration sensor is suitable for being inserted into the second threaded hole (221).
5. The fixing device of the high-frequency acceleration sensor of the gas turbine according to claim 4, characterized in that the second connecting member (21) and the second fixing seat (22) are integrally formed.
6. The fixing device of the high-frequency acceleration sensor of the gas turbine according to claim 1, characterized in that, the third bracket (3) comprises a third connecting piece (31) and a third fixing seat (32) which are connected;
At least two third through holes (311) are formed in the third connecting piece (31), and one third through hole (311) is used for being opposite to a screw hole in the flange surface (6) of one middle flange;
and a third threaded hole (321) is formed in the third fixed seat (32), and a screw rod on the high-frequency acceleration sensor is suitable for being inserted into the third threaded hole (321).
7. The fixing device of a high-frequency acceleration sensor of a gas turbine according to claim 6, characterized in that said third bracket (3) further comprises a second reinforcement rib (33);
the second reinforcing rib (33) is arranged on the third fixed seat (32) and connected with one side of the third connecting piece (31).
8. The fixing device of the high-frequency acceleration sensor of the gas turbine according to claim 1, characterized in that, the fourth bracket (4) comprises a fourth connecting piece (41) and a fourth fixing seat (42) which are connected;
at least two fourth through holes (411) are formed in the fourth connecting piece (41), and one fourth through hole (411) is used for being opposite to a screw hole in the flange surface (7) of one rear flange;
A fourth threaded hole (421) is formed in the fourth fixing seat (42), and a screw rod on the high-frequency acceleration sensor is suitable for being inserted into the fourth threaded hole (421).
9. the fixing device of a high-frequency acceleration sensor of a gas turbine according to claim 8, characterized in that said fourth bracket (4) further comprises a third reinforcing rib (43);
The third reinforcing rib (43) is arranged on the fourth fixed seat (42) and connected with one side of the fourth connecting piece (41).
10. The gas turbine high frequency acceleration sensor fixing device according to claim 1, characterized in that, the fixing device further comprises: a plurality of bolts;
The plurality of bolts is adapted to cooperate with the first bracket (1), the second bracket (2), the third bracket (3) and the fourth bracket (4).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920101507.4U CN209743039U (en) | 2019-01-21 | 2019-01-21 | Fixing device of high-frequency acceleration sensor of gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920101507.4U CN209743039U (en) | 2019-01-21 | 2019-01-21 | Fixing device of high-frequency acceleration sensor of gas turbine |
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| CN209743039U true CN209743039U (en) | 2019-12-06 |
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| CN201920101507.4U Active CN209743039U (en) | 2019-01-21 | 2019-01-21 | Fixing device of high-frequency acceleration sensor of gas turbine |
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