CN112446146A - Wiring and verification method suitable for high-pressure turbine blade vibration stress measurement test - Google Patents
Wiring and verification method suitable for high-pressure turbine blade vibration stress measurement test Download PDFInfo
- Publication number
- CN112446146A CN112446146A CN202011310654.6A CN202011310654A CN112446146A CN 112446146 A CN112446146 A CN 112446146A CN 202011310654 A CN202011310654 A CN 202011310654A CN 112446146 A CN112446146 A CN 112446146A
- Authority
- CN
- China
- Prior art keywords
- pressure turbine
- turbine disc
- disc
- wiring
- wiring method
- 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.)
- Granted
Links
- 238000000034 method Methods 0.000 title claims abstract description 41
- 238000005259 measurement Methods 0.000 title claims abstract description 15
- 238000012360 testing method Methods 0.000 title claims abstract description 15
- 238000012795 verification Methods 0.000 title claims abstract description 13
- 238000012545 processing Methods 0.000 claims abstract description 5
- WABPQHHGFIMREM-UHFFFAOYSA-N lead(0) Chemical compound [Pb] WABPQHHGFIMREM-UHFFFAOYSA-N 0.000 claims description 15
- 238000007789 sealing Methods 0.000 claims description 12
- 229910001220 stainless steel Inorganic materials 0.000 claims description 5
- 239000010935 stainless steel Substances 0.000 claims description 5
- 238000004458 analytical method Methods 0.000 claims description 4
- 238000006073 displacement reaction Methods 0.000 claims description 3
- 238000004080 punching Methods 0.000 claims description 3
- 230000007704 transition Effects 0.000 claims description 3
- 238000005516 engineering process Methods 0.000 claims description 2
- 239000000463 material Substances 0.000 abstract description 3
- 230000009467 reduction Effects 0.000 abstract description 3
- 239000007789 gas Substances 0.000 description 9
- 238000010586 diagram Methods 0.000 description 6
- 238000013461 design Methods 0.000 description 5
- 230000008569 process Effects 0.000 description 3
- 238000011161 development Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000004364 calculation method Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
Images
Classifications
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
- G06F30/23—Design optimisation, verification or simulation using finite element methods [FEM] or finite difference methods [FDM]
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
- G06F2119/14—Force analysis or force optimisation, e.g. static or dynamic forces
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Theoretical Computer Science (AREA)
- Computer Hardware Design (AREA)
- Evolutionary Computation (AREA)
- Geometry (AREA)
- General Engineering & Computer Science (AREA)
- General Physics & Mathematics (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention relates to a wiring and verification method suitable for a high-pressure turbine blade vibration stress measurement test, and belongs to the technical field of gas turbine engines. Compared with the existing wiring scheme, the scheme can improve the working reliability of the lead, improves the manufacturability of product processing and assembly, verifies that the modified high-pressure turbine disc meets the material strength requirement through strength check, and does not cause the reduction of the overall strength of the high-pressure turbine disc due to the addition of holes under the test condition.
Description
Technical Field
The invention belongs to the technical field of gas turbine engines, and particularly relates to a wiring and verification method suitable for a high-pressure turbine blade vibration stress measurement test.
Background
The turbine blade is an important part in a gas turbine engine, rotates at high rotation speed in high-temperature and high-pressure gas, and has great influence on the safe operation of the engine due to the service life and reliability of the turbine blade. In actual working conditions of the turbine blade, due to the connection rigidity of the blade and the disk and the influence of centrifugal force, temperature, gas force and the like, the dynamic frequency (natural vibration frequency) of the blade in a rotating state is different from the static frequency of the blade in a non-rotating state, and therefore, the dynamic stress measurement of the blade must be researched.
FIG. 1 is a partial cross-sectional view of a high pressure turbine rotor of a certain type of engine, and blade vibration stress measurement is performed on the turbine rotor structure. The patch positions of the strain gauges are as shown in figure 2, 6 strain gauges are uniformly distributed and selected in the circumferential direction to be arranged, and two positions are arranged on the basin side of each blade.
With the adoption of key technologies such as a high-temperature strain gauge, a slip ring current-leading device with high working speed and the like, the dynamic measurement of the vibration stress of the turbine blade under the conditions of high temperature and high rotating speed is possible. The blade dynamic measurement needs instruments and meters with complex structures, and durability, temperature resistance and vibration resistance. During measurement, the failure of the strain gauge and the electrical leading device under high-temperature airflow and strong vibration often causes test interruption, and the fracture and crack faults of the engine blade cannot be predicted in time as a result, so that the development period is prolonged, and the unnecessary loss in development is brought. Therefore, the reliable structural design is an effective guarantee for the success of the dynamic test, and the stability of the auxiliary structures such as instruments and meters and the like in the test process is guaranteed through the innovative design of the structure, so that the test success rate and the data reliability are improved.
In the blade vibration stress measurement scheme, a strain gauge lead needs to be welded on the surface of a turbine disc, the lead is led into the axis of a turbine through structural design, then the lead reaches the front end of a rotor and is connected with a slip ring power lead, and finally the lead is output from a power lead terminal and enters a test system. Fig. 3 is a schematic diagram of a conventional wiring scheme.
The existing wiring scheme is shown as a black thick solid line in figure 3, a mode of leading wires from a front cavity of a high-pressure turbine disc (3) is adopted, holes do not need to be formed in a rear grate ring of the disc, and the risk of leakage of high-temperature gas to a bearing cavity is reduced. However, the blade (1) needs to pass through an axial gap between the high-pressure turbine guider and the turbine blade, in order to avoid the problem that a lead wire (which is bent too much and needs to be notched at the air inlet edge of a blade edge plate, high-temperature gas flows backward, the temperature of the gas where the lead wire is located is higher, and the reliability is reduced, after the lead wire is coiled, lead wire holes need to be formed in the high-pressure turbine disk (3) and the high-pressure turbine shaft (5) (a shaft sleeve 6 is arranged in the lead wire holes), a ring sleeve (4) and the high-pressure turbine shaft (5) pressed on the high-pressure turbine disk (3) need to be disassembled when the lead wire holes are machined, the lead wire is reassembled after the holes, dynamic balance is achieved, and the assembly is complicated.
Disclosure of Invention
Technical problem to be solved
The technical problem to be solved by the invention is as follows: how to design a wiring and strength verification method capable of meeting the dynamic measurement of the vibration stress of the high-pressure turbine blade.
(II) technical scheme
In order to solve the technical problem, the invention provides a wiring method suitable for a high-pressure turbine blade vibration stress measurement test, which is realized by adopting a high-pressure turbine disc 3 back cavity lead wire mode and comprises the following steps:
firstly, the structure of the high-pressure turbine rotor is processed as follows:
1) the low-pressure turbine guide 7 is cut in the circumferential direction and is in smooth transition, and the head of a screw 8 used for fixing the labyrinth sleeve on the low-pressure turbine casing is turned, so that the axial clearance between the high-pressure turbine disc 3 and the low-pressure turbine guide 7 is increased; the labyrinth sleeve is matched with a sealing labyrinth at the rear part of the high-pressure turbine disc 3;
2) a plurality of annular grooves are formed in the sealing labyrinth at the rear part of the high-pressure turbine disc 3;
3) a plurality of round holes are formed in a low stress area of a rear shaft neck of the high-pressure turbine disc 3, and sharp edges are rounded;
4) processing the clearance on the inner surface of the lathed ring sleeve 4, and enlarging the gap between the ring sleeve 4 and the rear shaft neck of the high-pressure turbine disc 3;
after the treatment based on the structure, the wiring is carried out, and the lead wire sequentially passes through the gap between the blade 1 and the low-pressure turbine guider 7, the sealing labyrinth at the rear part of the high-pressure turbine disc 3, and the gap between the ring sleeve 4 and the high-pressure turbine disc 3.
Preferably, when the structure of the high-pressure turbine rotor is processed, a stainless steel sheet is welded in an annular groove at the sealing labyrinth after the lead wire is led out.
Preferably, when the structure of the high-pressure turbine rotor is processed, six annular grooves are formed in the sealing labyrinth at the rear part of the high-pressure turbine disc 3.
Preferably, the structure of the high pressure turbine rotor is treated by opening six circular holes in the rear journal low stress region of the high pressure turbine disk 3.
Preferably, the structure of the high pressure turbine rotor is treated by making six circular holes with a diameter of 4.5 mm in the rear journal low stress region of the high pressure turbine disc 3.
The invention also provides a method for intensity check based on the wiring method, in the method, ansys is adopted for intensity check, the stress distribution of the punching position of the high-pressure turbine rotor after treatment is analyzed, and the intensity of the high-pressure turbine disc 3 is verified.
Preferably, in the method, the high-pressure turbine disc 3 is modeled firstly, and the high-pressure turbine disc 3 model is simplified during modeling, and the specific modeling method is as follows:
and 3, based on the symmetrical characteristic of the high-pressure turbine disc 3, only selecting 1/6 of the high-pressure turbine disc 3 for analysis.
Preferably, in the method, the quality of the mesh at the position where stress concentration is expected to occur is ensured when the mesh is divided.
Preferably, in the method, the boundary conditions applied to the model of the high-pressure turbine disc 3 include:
the equivalent force of the inertia force of the blade 1, the locking plate and the tenon is exerted on the upper surface of the outer edge of the high-pressure turbine disc 3;
applying a rotational inertia force to the whole high-pressure turbine disk 3;
applying symmetry constraints on the symmetry plane;
and selecting a node to restrain the axial rigid displacement restraint.
The invention also provides an application of the wiring method in the technical field of gas turbine engines.
(III) advantageous effects
The invention provides a wiring and strength verification method capable of meeting dynamic measurement of vibration stress of a high-pressure turbine blade, wherein a strain gauge lead is positioned in a rear cavity of a high-pressure turbine disc, and is positioned at an environment with a higher temperature and a front cavity of the high-pressure turbine disc with a lower temperature by 80-100K, so that the working stability of the lead is improved; the lead holes are all positioned on the high-pressure turbine disc, so that balance and assembly are facilitated; in order to seal the holes on the grate ring, a stainless steel sheet is welded at the grate ring, and the stainless steel sheet has the risk of flying out under the condition of high rotating speed due to light weight, so that the high-temperature gas temperature suffered by the strain gauge lead is further reduced, and the reliability is improved.
Drawings
FIG. 1 is a sectional view of a prior art high pressure turbine rotor area;
FIG. 2 is a schematic diagram of a bonding position of a strain gauge in a conventional high-pressure turbine rotor;
FIG. 3 is a schematic diagram of a prior art wiring scheme;
FIG. 4 is a schematic diagram of a wiring scheme of the present invention;
FIG. 5 is a simplified schematic diagram of a model in the strength verification process of the present invention;
FIG. 6 is a schematic diagram of a finite element mesh generated during the strength verification process of the present invention;
FIG. 7 is a graph of the stress distribution of a circular hole obtained by the strength verification method of the present invention;
fig. 8 is a graph of the local stress distribution of the long hole obtained by the strength verification method of the present invention.
Detailed Description
In order to make the objects, contents, and advantages of the present invention clearer, the following detailed description of the embodiments of the present invention will be made in conjunction with the accompanying drawings and examples.
According to the wiring method suitable for the high-pressure turbine blade vibration stress measurement test, in order to protect the lead wire of the strain gauge 2, a mode of a lead wire of a rear cavity of a high-pressure turbine disc 3 is adopted, and a specific wiring scheme is shown by a black dotted line in fig. 4. In the wiring method, a lead wire sequentially passes through a gap between the blade 1 and the low-pressure turbine guider 7, a sealing labyrinth at the rear part of the high-pressure turbine disc 3 and a gap between the ring sleeve 4 and the high-pressure turbine disc 3, and based on the wiring method, the structure of the high-pressure turbine rotor needs to be processed as follows:
1) the low-pressure turbine guide 7 is cut in the circumferential direction and is in smooth transition, and the screw 8 used for fixing the labyrinth sleeve on the low-pressure turbine casing is turned at the head part as shown by rectangular wire frame areas in 7 and 8, so that the axial clearance between the high-pressure turbine disc 3 and the low-pressure turbine guide 7 is increased; the labyrinth sleeve is matched with a sealing labyrinth at the rear part of the high-pressure turbine disc 3;
2) six annular grooves are formed in the sealing labyrinth at the rear part of the high-pressure turbine disc 3, and a stainless steel sheet is welded behind a lead, so that backflow of fuel gas is reduced;
3) six round holes with the diameter of 4.5 mm are formed in the low stress area of the rear shaft neck of the high-pressure turbine disc 3, and sharp edges are rounded;
4) the inner surface of the lathed ring sleeve 4 is shown as a rectangular wire frame area in 4, so that a gap between the ring sleeve 4 and the rear shaft neck of the high-pressure turbine disc 3 is enlarged, and the lead of the strain gauge 2 is convenient.
Based on the wiring method, ansys is adopted to carry out strength check, the stress distribution of the punching position of the high-pressure turbine rotor after treatment is analyzed, and the strength of the high-pressure turbine disc 3 is verified. The high-pressure turbine disk 3 mainly bears the inertial load generated by the rotation of the blades 1, the locking plates, the wind-blocking plates and the high-pressure turbine disk 3. For convenient modeling, the high-pressure turbine disc 3 model is simplified on the basis of not influencing the analysis result of the main part, and the specific modeling method comprises the following steps:
And 2, removing partial characteristics which have small influence on the concerned part, including holes on the flange plate, rounding and axial extension parts of the shaft, and obtaining a high-pressure turbine disc 3 model as shown in fig. 5.
And 3, considering the symmetrical characteristic of the high-pressure turbine disc 3, only selecting 1/6 of the high-pressure turbine disc 3 for analysis.
When the grid is divided, the grid quality of the part where stress concentration is expected to occur is ensured. The whole grid and the partial grid are shown in fig. 6.
The boundary conditions applied to the high-pressure turbine disk 3 model include:
1. the equivalent force of the inertia force of the blade 1, the locking plate and the tenon is exerted on the upper surface of the outer edge of the high-pressure turbine disc 3;
2. applying rotation inertia force on the whole high-pressure turbine disc 3, wherein the angular speed is 50000 r/m;
3. applying symmetry constraints on the symmetry plane;
4. and selecting a node to restrain the axial rigid displacement restraint.
After calculation, the stress distribution of the high-pressure turbine disc 3 is shown in fig. 7-8, and it can be found that a small range of yielding occurs on the surface of the hole near both holes, the maximum stress of the hole is smaller than the tensile limit of the material, and the stress distribution has a larger safety factor. Therefore, the increase of the holes under the test condition does not cause the reduction of the overall strength of the high-pressure turbine disc 3, and the design of the holes is satisfactory.
Compared with the existing wiring scheme, the scheme can improve the working reliability of the lead, improves the manufacturability of product processing and assembly, verifies that the modified high-pressure turbine disc meets the material strength requirement through strength check, and does not cause the reduction of the overall strength of the high-pressure turbine disc due to the addition of holes under the test condition.
The above description is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, several modifications and variations can be made without departing from the technical principle of the present invention, and these modifications and variations should also be regarded as the protection scope of the present invention.
Claims (10)
1. A wiring method suitable for a high-pressure turbine blade vibration stress measurement test is characterized by being realized in a mode of a high-pressure turbine disk (3) rear cavity lead wire, and comprises the following steps:
firstly, the structure of the high-pressure turbine rotor is processed as follows:
1) the low-pressure turbine guide device (7) is subjected to circumferential cutting and smooth transition, a screw (8) used for fixing the labyrinth sleeve on the low-pressure turbine casing is subjected to head turning, and the axial clearance between the high-pressure turbine disc (3) and the low-pressure turbine guide device (7) is increased; the labyrinth sleeve is matched with a sealing labyrinth at the rear part of the high-pressure turbine disc (3);
2) a plurality of annular grooves are formed in the sealing labyrinth at the rear part of the high-pressure turbine disc (3);
3) a plurality of round holes are formed in a low stress area of a rear shaft neck of the high-pressure turbine disc (3), and sharp edges are rounded;
4) processing the clearance on the inner surface of the lathed ring sleeve (4), and enlarging the gap between the ring sleeve (4) and the rear shaft neck of the high-pressure turbine disc (3);
after the structure is processed, wiring is carried out, and leads sequentially pass through a gap between the blade (1) and the low-pressure turbine guider (7), a sealing labyrinth at the rear part of the high-pressure turbine disc (3), and a gap between the ring sleeve (4) and the high-pressure turbine disc (3).
2. The wiring method according to claim 1, wherein the structure of the high pressure turbine rotor is processed, and a stainless steel thin plate is welded in an annular groove at the sealing labyrinth after the lead wire.
3. Wiring method according to claim 2, characterized in that six ring grooves are made at the obturating labyrinth at the rear of the high pressure turbine disc (3) when the structure of the high pressure turbine rotor is processed.
4. Wiring method according to claim 3, characterized in that the structure of the high pressure turbine rotor is treated by making six circular holes in the rear journal low stress area of the high pressure turbine disc (3).
5. Wiring method according to claim 4, characterized in that the structure of the high pressure turbine rotor is treated by opening six circular holes with a diameter of 4.5 mm in the rear journal low stress zone of the high pressure turbine disc (3).
6. A method of intensity verification based on the wiring method according to any one of claims 1 to 5, wherein intensity verification is performed using ansys, and the intensity verification is performed on the high-pressure turbine disk (3) by analyzing the stress distribution at the punching position of the high-pressure turbine rotor after processing.
7. Wiring method according to claim 6, characterized in that in the method, modeling of the high pressure turbine disk (3) is performed first, and during modeling, the model of the high pressure turbine disk (3) is simplified, and the specific modeling method is as follows:
the method comprises the following steps that 1, tenons of a high-pressure turbine disc (3) are cut off, and inertial loads generated by rotation of the tenons, blades (1), locking plates and wind shielding plates are converted into equivalent surface forces to be applied to the outer surface of the high-pressure turbine disc (3) after the tenons are cut off;
step 2, removing partial characteristics which have small influence on the concerned position, including holes on a flange plate, rounding and axial extension parts of a shaft, so as to obtain a high-pressure turbine disk (3) model;
and 3, based on the symmetrical characteristic of the high-pressure turbine disc (3), only selecting 1/6 of the high-pressure turbine disc (3) for analysis.
8. The wiring method according to claim 7, wherein in the method, the mesh quality at a portion where stress concentration is expected to occur is ensured when the mesh is divided.
9. Wiring method according to claim 8, characterized in that in the method the boundary conditions applied to the model of the high-pressure turbine disc (3) comprise:
the inertia force of the blade (1), the locking plate and the tenon is exerted on the upper surface of the outer edge of the high-pressure turbine disc (3);
the high-pressure turbine disc (3) is integrally applied with a rotation inertia force;
applying symmetry constraints on the symmetry plane;
and selecting a node to restrain the axial rigid displacement restraint.
10. Use of the wiring method according to any one of claims 1 to 5 in the field of gas turbine engine technology.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011310654.6A CN112446146B (en) | 2020-11-20 | 2020-11-20 | Wiring and verification method suitable for high-pressure turbine blade vibration stress measurement test |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011310654.6A CN112446146B (en) | 2020-11-20 | 2020-11-20 | Wiring and verification method suitable for high-pressure turbine blade vibration stress measurement test |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112446146A true CN112446146A (en) | 2021-03-05 |
| CN112446146B CN112446146B (en) | 2023-11-03 |
Family
ID=74737670
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011310654.6A Active CN112446146B (en) | 2020-11-20 | 2020-11-20 | Wiring and verification method suitable for high-pressure turbine blade vibration stress measurement test |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112446146B (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113565583A (en) * | 2021-07-19 | 2021-10-29 | 中国航发沈阳发动机研究所 | Device for testing dynamic stress of complete high-pressure turbine rotor of double-rotor turbofan engine |
| CN113607330A (en) * | 2021-07-26 | 2021-11-05 | 中国船舶重工集团公司第七0三研究所 | Method for measuring pressure of turbine chamber of marine gas turbine |
| CN113624357A (en) * | 2021-07-26 | 2021-11-09 | 中国船舶重工集团公司第七0三研究所 | Method for measuring temperature of turbine chamber of marine gas turbine |
| CN113844677A (en) * | 2021-10-25 | 2021-12-28 | 中国航发沈阳发动机研究所 | Axial lead structure for measuring dynamic stress of whole high-pressure turbine of turbofan engine |
| CN113984399A (en) * | 2021-10-27 | 2022-01-28 | 中国航发沈阳发动机研究所 | Pressure test device and method for inner ring of turbine guider of aircraft engine |
| CN114166393A (en) * | 2021-11-10 | 2022-03-11 | 中国航发湖南动力机械研究所 | Blade dynamic stress measuring structure |
| CN116124464A (en) * | 2023-04-17 | 2023-05-16 | 中国航发四川燃气涡轮研究院 | Rim lead structure for measuring dynamic stress of multistage turbine blades and design method |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH08158805A (en) * | 1994-12-06 | 1996-06-18 | Ishikawajima Harima Heavy Ind Co Ltd | Damper structure for turbine rotor blade |
| EP1707748A2 (en) * | 2005-04-01 | 2006-10-04 | Hitachi, Ltd. | Mounting of blades in a steam turbine rotor |
| US20170058675A1 (en) * | 2015-08-31 | 2017-03-02 | Rolls-Royce Corporation | Low diameter turbine rotor clamping arrangement |
| CN111060271A (en) * | 2019-10-29 | 2020-04-24 | 北京动力机械研究所 | Dynamic test method for vibration stress of turbine blade of small turbine engine |
-
2020
- 2020-11-20 CN CN202011310654.6A patent/CN112446146B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH08158805A (en) * | 1994-12-06 | 1996-06-18 | Ishikawajima Harima Heavy Ind Co Ltd | Damper structure for turbine rotor blade |
| EP1707748A2 (en) * | 2005-04-01 | 2006-10-04 | Hitachi, Ltd. | Mounting of blades in a steam turbine rotor |
| US20170058675A1 (en) * | 2015-08-31 | 2017-03-02 | Rolls-Royce Corporation | Low diameter turbine rotor clamping arrangement |
| CN111060271A (en) * | 2019-10-29 | 2020-04-24 | 北京动力机械研究所 | Dynamic test method for vibration stress of turbine blade of small turbine engine |
Non-Patent Citations (7)
| Title |
|---|
| 刘风坤;贾;: "航空发动机高压涡轮转子试验段静强度研究", 中国设备工程, no. 09 * |
| 周拜豪;尹红顺;苏廷铭;任铭林;: "高性能前掠三级轴流风扇的设计与试验研究", 燃气涡轮试验与研究, no. 02 * |
| 曹昆华;黄家经;: "某型发动机低压涡轮转子叶片动测技术及应用研究", 燃气涡轮试验与研究, no. 01 * |
| 栾永先;赵光电;: "某涡轮性能试验件结构设计", 航空发动机, no. 05 * |
| 王奉明;贺进;朱俊强;: "高转速小尺寸涡轮叶片动应力测量方法与应用", 推进技术, no. 06 * |
| 费成巍;白广忱;范觉超;: "高压涡轮瞬态叶尖径向运行间隙计算分析", 航空制造技术, no. 19 * |
| 陈礼顺;王彦岭;卢建红;张辉;: "航空发动机封严技术的研究和应用进展", 航空制造技术, no. 08 * |
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113565583A (en) * | 2021-07-19 | 2021-10-29 | 中国航发沈阳发动机研究所 | Device for testing dynamic stress of complete high-pressure turbine rotor of double-rotor turbofan engine |
| CN113565583B (en) * | 2021-07-19 | 2022-08-19 | 中国航发沈阳发动机研究所 | Device for testing dynamic stress of complete high-pressure turbine rotor of double-rotor turbofan engine |
| CN113607330A (en) * | 2021-07-26 | 2021-11-05 | 中国船舶重工集团公司第七0三研究所 | Method for measuring pressure of turbine chamber of marine gas turbine |
| CN113624357A (en) * | 2021-07-26 | 2021-11-09 | 中国船舶重工集团公司第七0三研究所 | Method for measuring temperature of turbine chamber of marine gas turbine |
| CN113844677A (en) * | 2021-10-25 | 2021-12-28 | 中国航发沈阳发动机研究所 | Axial lead structure for measuring dynamic stress of whole high-pressure turbine of turbofan engine |
| CN113844677B (en) * | 2021-10-25 | 2024-03-19 | 中国航发沈阳发动机研究所 | Axial lead structure for dynamic stress measurement of whole high-pressure turbine of turbofan engine |
| CN113984399A (en) * | 2021-10-27 | 2022-01-28 | 中国航发沈阳发动机研究所 | Pressure test device and method for inner ring of turbine guider of aircraft engine |
| CN113984399B (en) * | 2021-10-27 | 2023-09-05 | 中国航发沈阳发动机研究所 | Device and method for testing inner ring pressure of turbine guider of aero-engine |
| CN114166393A (en) * | 2021-11-10 | 2022-03-11 | 中国航发湖南动力机械研究所 | Blade dynamic stress measuring structure |
| CN114166393B (en) * | 2021-11-10 | 2023-06-20 | 中国航发湖南动力机械研究所 | Blade dynamic stress measuring structure |
| CN116124464A (en) * | 2023-04-17 | 2023-05-16 | 中国航发四川燃气涡轮研究院 | Rim lead structure for measuring dynamic stress of multistage turbine blades and design method |
| CN116124464B (en) * | 2023-04-17 | 2023-08-18 | 中国航发四川燃气涡轮研究院 | Rim lead structure for measuring dynamic stress of multistage turbine blades and design method |
Also Published As
| Publication number | Publication date |
|---|---|
| CN112446146B (en) | 2023-11-03 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN112446146A (en) | Wiring and verification method suitable for high-pressure turbine blade vibration stress measurement test | |
| CN101592590B (en) | Fault indirect diagnosis technique of rotating blade | |
| Megerle et al. | Numerical and experimental investigation of the aerodynamic excitation of a model low-pressure steam turbine stage operating under low volume flow | |
| US20110070072A1 (en) | Rotary machine tip clearance control mechanism | |
| US6932560B2 (en) | Apparatus and method for detecting an impact on a rotor blade | |
| US20100080689A1 (en) | Gas turbine engine rotor and balance weight therefor | |
| US10546078B2 (en) | Turbofan case for controlling blade deflection | |
| US9327341B2 (en) | Method of fabricating integrally bladed rotor and stator vane assembly | |
| US20160208612A1 (en) | Rotor disk boss | |
| EP2803821A1 (en) | Blade device, blade system, and corresponding method of manufacturing a blade system | |
| JP2016104980A (en) | Blisk rim face undercut | |
| JP2017101663A (en) | Methods and systems for detecting wear in turbine engine | |
| US10385865B2 (en) | Airfoil tip geometry to reduce blade wear in gas turbine engines | |
| RU2377415C2 (en) | Method and device to reveal state of rotor incorporated with machine converting flow kinetic energy into mechanical power | |
| Rusinski et al. | Monitoring and testing of high power industrial fans vibration | |
| US11542820B2 (en) | Turbomachinery blade and method of fabricating | |
| US20170306919A1 (en) | Rotating machine and installation for converting energy comprising such a machine | |
| CN113125158B (en) | Device for fixing detected shrouded blade and shrouded blade detection equipment | |
| Siewert et al. | Advanced Last Stage Blade for Nuclear Power Plant Upgrades | |
| Troha et al. | Composite Inlays Increase Flutter Resistance of Turbine Engine Fan Blades | |
| Mariottini et al. | Wheel box test aeromechanical verification of new first stage bucket with integrated cover plates for MS5002 GT | |
| RU2033525C1 (en) | Welded drum-type rotor of turbomachine | |
| CN116124464B (en) | Rim lead structure for measuring dynamic stress of multistage turbine blades and design method | |
| Gao et al. | Engine vibration certification | |
| EP4137703A1 (en) | Impeller shroud frequency tuning rib |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |