CN115680902A - Method for adjusting axial force of rotor of aircraft engine - Google Patents
Method for adjusting axial force of rotor of aircraft engine Download PDFInfo
- Publication number
- CN115680902A CN115680902A CN202211256133.6A CN202211256133A CN115680902A CN 115680902 A CN115680902 A CN 115680902A CN 202211256133 A CN202211256133 A CN 202211256133A CN 115680902 A CN115680902 A CN 115680902A
- Authority
- CN
- China
- Prior art keywords
- axial force
- engine
- adjusting
- rotor
- force
- 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 36
- 238000013461 design Methods 0.000 claims abstract description 15
- 238000000605 extraction Methods 0.000 claims abstract description 8
- 238000004458 analytical method Methods 0.000 claims abstract description 5
- 238000010206 sensitivity analysis Methods 0.000 claims abstract description 4
- 238000004146 energy storage Methods 0.000 claims description 24
- 239000000463 material Substances 0.000 claims description 7
- 208000002925 dental caries Diseases 0.000 claims description 3
- 238000002955 isolation Methods 0.000 claims description 3
- 230000009467 reduction Effects 0.000 claims description 3
- 238000005086 pumping Methods 0.000 claims description 2
- 238000012360 testing method Methods 0.000 abstract description 6
- 230000008569 process Effects 0.000 abstract description 4
- 230000008859 change Effects 0.000 description 4
- 238000011161 development Methods 0.000 description 3
- 238000007429 general method Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 230000009897 systematic effect Effects 0.000 description 2
- 230000002159 abnormal effect Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000740 bleeding effect Effects 0.000 description 1
- 238000004364 calculation method Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Images
Landscapes
- Testing Of Engines (AREA)
Abstract
The invention provides an axial force adjusting method for an aircraft engine rotor, which comprises the following steps of S1, obtaining a part influencing the axial force of the engine rotor; s2, designing measures for adjusting axial force of the engine rotor, including passive clearance throttling and pressure reducing adjustment, disc surface pressure extraction adjustment and power compensation adjustment; s3, performing axial force sensitivity analysis by adopting an axial force analysis model according to the configuration of the engine, and judging the axial force of the engine rotor and the axial force threshold value; and S4, selecting one or more axial force adjusting measures in the S2 based on the judgment result in the S3, and adjusting the axial force. The axial force adjusting method designed by the invention can meet the requirements of axial force adjustment and pressure balance design of different types of aircraft engines, provides guidance for axial force adjustment in the process of developing the aircraft engines, effectively reduces the risk of developing the aircraft engines, and improves the test safety and reliability of the engines.
Description
Technical Field
The invention belongs to the field of aero-engines, relates to an engine load calculation and pressure balance design technology, and particularly relates to an aero-engine rotor axial force adjustment method which can meet requirements of axial force adjustment and pressure balance design of aero-engines of different models.
Background
The pressure balance design of the aircraft engine plays an important role in development, wherein the axial force design is a key link, the axial force of the engine needs to be kept at a reasonable working level so as to ensure the condition that light load and reversing cannot be carried out in the working process, and when the axial force design is abnormal, the working reliability and integrity of the aircraft engine are influenced.
At present, no systematic adjustment method for the axial force of the domestic aero-engine exists, local adjustment is carried out according to a test result after a complete machine test is carried out abroad, the axial force adjustment is a systematic problem in the design of aero-engine pressure balance, the local adjustment mode cannot achieve the expected purpose once, multiple times of adjustment are needed, and unpredictable influence is caused on the test safety and reliability.
Disclosure of Invention
The invention aims to design an axial force adjusting method of an aircraft engine rotor, which can meet the requirements of axial force adjustment and pressure balance design of aircraft engines of different models, provide guidance for axial force adjustment in the process of aircraft engine development, effectively reduce the risk of aircraft engine development, and improve the test safety and reliability of the engines.
The technical scheme for realizing the purpose of the invention is as follows: an aircraft engine rotor axial force adjusting method comprises the following steps:
s1, obtaining a component influencing the axial force of an engine rotor;
s2, designing measures for adjusting axial force of the engine rotor, including passive clearance throttling and pressure reducing adjustment, disc surface pressure extraction adjustment and power compensation adjustment;
s3, performing axial force sensitivity analysis by adopting an axial force analysis model according to the configuration of the engine, and judging the axial force of the engine rotor and the axial force threshold value;
and S4, selecting one or more axial force adjusting measures in the S2 based on the judgment result in the S3, and adjusting the axial force.
Further, the passive gap throttling and pressure reducing adjusting method comprises the following steps: the thermal expansion coefficient of the engine stator material is selected to be smaller than that of the engine rotor material, so that the clearance value between the engine rotor and the engine stator in work is reduced, and the axial force of the rotor adjusted by local disc cavity pressure is reduced.
Further, the method for adjusting the drawing pressure of the disk surface comprises the following steps: set up isolation structure near engine turntable surface position, divide the carousel chamber into 2 independent cavitys, each independent cavity carries out independent exhaust respectively, carries out the local step-down that bleeds to the position that is close to engine turntable to reduce this position dish chamber axial force of carousel chamber quotation partial pressure reduction.
Further, the power compensation adjustment method comprises:
designing an energy storage device, wherein one end of the energy storage device is connected with an aircraft engine, and the other end of the energy storage device is connected with an aircraft accessory or an engine accessory;
when the axial force of the engine rotor meets the design requirement, the engine rotor stores the input power of the energy storage device through power extraction;
when the axial force of the engine rotor is smaller than the minimum threshold value of the axial force, and simultaneously when the meshing force and the axial force are in the same direction, the energy storage device inputs work through the gear, and the meshing force is increased to increase the axial force; or when the meshing force is opposite to the axial force, the energy storage device outputs power to the airplane accessory, and at the moment, the power is not extracted by the engine any more so as to increase the axial force;
when the axial force of the engine rotor is larger than the maximum threshold value of the axial force, and simultaneously when the meshing force and the axial force are in the same direction, the energy storage device outputs power to the aircraft accessory, and at the moment, the engine does not extract power to reduce the axial force; or when the meshing force is opposite to the axial force, the energy storage device inputs work to the gear, and the meshing force is increased to achieve the purpose of reducing the axial force.
In an improved embodiment of the method for adjusting the axial force of the aircraft engine rotor, in the step S2, the axial force adjusting means further includes one or more of increasing a labyrinth area, adjusting a mechanical adjustable area, adding a bleed air pressurization flow path, exhausting and releasing pressure, a variable throttling unit, and adjusting a meshing force direction.
Further, the method for adjusting the axial force of the aircraft engine rotor further comprises a step S5 of verifying and evaluating the adjusted axial force of the engine.
Compared with the prior art, the invention has the beneficial effects that: the method for adjusting the axial force of the rotor of the aero-engine designed by the invention can meet the requirements of axial force adjustment and pressure balance design of aero-engines of different models, provides guidance for the adjustment of the axial force in the process of developing the aero-engine, effectively reduces the risk of developing the aero-engine, and improves the test safety and reliability of the engine.
Drawings
In order to more clearly illustrate the technical solution of the embodiments of the present invention, the drawings used in the description of the embodiments will be briefly introduced below. It should be apparent that the drawings in the following description are only for illustrating the embodiments of the present invention or technical solutions in the prior art more clearly, and that other drawings can be obtained by those skilled in the art without any inventive work.
FIG. 1 is a flow chart of a method of adjusting an axial force of an aircraft engine rotor according to the present invention;
FIG. 2 is a block diagram of an engine rotor axial force adjustment strategy according to an exemplary embodiment;
FIG. 3 is a schematic diagram of power compensation adjustment in the measure for adjusting the axial force of the rotor of the engine according to an embodiment.
Detailed Description
The invention will be further described with reference to specific embodiments, and the advantages and features of the invention will become apparent as the description proceeds. These examples are illustrative only and do not limit the scope of the present invention in any way. It will be understood by those skilled in the art that various changes in form and details may be made therein without departing from the spirit and scope of the invention, and that such changes and substitutions are intended to be within the scope of the invention.
In the description of the present embodiments, it is to be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of describing the present invention and simplifying the description, but do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the present invention.
Furthermore, the terms "first," "second," "third," and the like are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicit to a number of indicated technical features. Thus, a feature defined as "first," "second," etc. may explicitly or implicitly include one or more of that feature. In the description of the invention, the meaning of "a plurality" is two or more unless otherwise specified.
The specific embodiment provides an adjusting method for axial force of an aircraft engine rotor, and as shown in fig. 1, the adjusting method comprises the following steps:
s1, obtaining a component influencing the axial force of the engine rotor.
The method for determining the components influencing the axial force of the engine rotor comprises the following steps: the axial force of the rotor of the aircraft engine is analyzed and screened by establishing an engine rotor axial force analysis model, the analyzed axial force of the rotor of the aircraft engine mainly comprises a disc cavity axial force, a runner axial force and a gear meshing force, and when the axial force of the aircraft engine is adjusted, the runner axial force is related to pneumatic parameters, and the adjustment is basically not performed after the pneumatic parameters are determined under the general condition, so that the runner axial force is not adjusted generally, and only the disc cavity axial force and the gear meshing force are adjusted generally.
The axial force of the disk cavity comprises axial force of a compressor/fan disk cavity and axial force of a high/low turbine cavity, wherein the axial force of the compressor/fan disk cavity is generated by a front bearing cavity, a compressor/fan disk front cavity, a compressor/fan disk rear cavity and a drum shaft; the high/low turbine cavity axial force is generated by a high/low turbine front cavity, a high/low turbine rear cavity and a rear bearing cavity.
Where the engagement force is generated by aircraft/engine accessory power extraction.
S2, designing measures for adjusting the axial force of the engine rotor, including passive clearance throttling and pressure reducing adjustment, disc surface pressure drawing adjustment and power compensation adjustment.
Generally speaking, the axial force of the engine can be adjusted from three directions of area, pressure and meshing force, and different adjustment directions have different adjustment measures, for example, referring to fig. 2, the area adjustment direction includes adjusting the labyrinth adjustment area, adjusting the mechanical adjustable area, and the like; the pressure adjusting direction comprises adjusting a bleed air pressurizing flow path, adjusting bleed air pressurizing, throttling and depressurizing a passive gap, exhausting and relieving pressure, pumping pressure on the disc surface, a variable throttling unit and the like; the meshing force adjusting direction comprises meshing force direction adjustment, power compensation and the like.
The area adjustment direction is a conventional general method, and will not be described in detail here.
In the aspect of adjusting the meshing force, the meshing force direction adjusting measure is an existing general method, which is not described in detail herein, and in this step, a power compensation adjusting method is mainly designed to adjust the axial force of the engine.
Specifically, referring to fig. 3, one method of adjusting the power compensation is as follows:
designing an energy storage device, wherein one end of the energy storage device is connected with an aircraft engine, and the other end of the energy storage device is connected with an aircraft accessory or an engine accessory;
when the axial force of the engine rotor meets the design requirement, the engine rotor stores the input power of the energy storage device through power extraction;
when the axial force of the engine rotor is smaller than the minimum threshold value of the axial force, and simultaneously when the meshing force and the axial force are in the same direction, the energy storage device inputs work through the gear, and the meshing force is increased to increase the axial force; or when the meshing force is opposite to the axial force, the energy storage device outputs power to the airplane accessory, and the engine does not extract power to increase the axial force;
when the axial force of the engine rotor is larger than the maximum threshold value of the axial force, and simultaneously when the meshing force and the axial force are in the same direction, the energy storage device outputs power to the airplane accessory, and at the moment, the engine does not extract power to reduce the axial force; or when the meshing force is opposite to the axial force, the energy storage device inputs work to the gear, and the meshing force is increased to achieve the purpose of reducing the axial force.
In the measures of adjusting the bleed air pressurization flow path, adjustable bleed air pressurization, passive gap throttling depressurization, exhaust pressure relief, disk surface pressure extraction, variable throttling units and the like in the pressure adjustment direction, the whole bleed air pressurization flow path, adjustable bleed air pressurization, exhaust pressure relief, variable throttling units and the like are all conventional general methods, and are not described in detail herein.
Specifically, the passive clearance throttling and pressure reducing adjusting method comprises the following steps: the thermal expansion coefficient of the engine stator material is selected to be smaller than that of the engine rotor material, so that the clearance value between the engine rotor and the engine stator in work is reduced, and the axial force of the rotor adjusted by local disc cavity pressure is reduced. In order to meet the design requirement of an air system of an aircraft engine, a comb-honeycomb structure is widely adopted between rotors and stators, and because the thermal inertia of the rotors is larger than that of the stators, the conditions of large axial force change range, overload or reversing caused by the fact that the pressure change of a disc cavity deviates from the design expectation are easy to occur along with the change of the working state of the engine. In order to solve the problem, the rotor and the stator are matched with materials with different thermal expansion coefficients, so that the thermal state deformation of the honeycomb structure is relatively reduced, the effects of large gap in a low state and relatively reduced gap in a high state of the engine are achieved, and the expectation of controllable pressure change of a disc cavity is realized.
Specifically, the method for adjusting the drawing pressure of the disk surface comprises the following steps: set up isolation structure near engine carousel surface position, divide the carousel chamber into 2 independent cavitys, each independent cavity carries out independent exhaust respectively, carries out the local step-down of bleeding to the position that is close to the engine carousel, reduces carousel chamber quotation local pressure and reduces this position dish chamber axial force.
And S3, adopting an axial force analysis model to perform axial force sensitivity analysis according to the engine configuration, and judging the axial force of the engine rotor and the axial force threshold value.
When the axial force of the engine rotor is larger than the minimum threshold value of the axial force, the axial force of the engine rotor needs to be reduced;
when the axial force of the engine rotor is less than the maximum threshold value of the axial force, the axial force of the engine rotor needs to be increased.
And S4, selecting one or more axial force adjusting measures in the S2 based on the judgment result in the S3, and adjusting the axial force.
In the step, according to the requirement of increasing or reducing the axial force of the engine rotor, the corresponding increasing or reducing measure in the step S2 is selected for adjustment.
In another embodiment of the present invention, after the axial force is adjusted through the above steps S1 to S4, as shown in fig. 1, it is necessary to verify and evaluate the adjusted axial force of the engine through step S5.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents, improvements and the like that fall within the spirit and principle of the present invention are intended to be included therein.
Furthermore, although the description is made in terms of embodiments, not every embodiment includes only a single embodiment, and such descriptions are merely for clarity and will be made by those skilled in the art as a whole, and the embodiments may be combined as appropriate to form other embodiments as would be understood by those skilled in the art.
Claims (6)
1. An aircraft engine rotor axial force adjusting method is characterized by comprising the following steps:
s1, obtaining a component influencing the axial force of an engine rotor;
s2, designing measures for adjusting axial force of the rotor of the engine, including passive clearance throttling and pressure reducing adjustment, disc surface pressure extraction adjustment and power compensation adjustment;
s3, according to the configuration of the engine, carrying out axial force sensitivity analysis by adopting an axial force analysis model, and judging the axial force of the rotor of the engine and the axial force threshold value;
and S4, selecting one or more axial force adjusting measures in the S2 based on the judgment result in the S3, and adjusting the axial force.
2. The method for adjusting the axial force of the aircraft engine rotor according to claim 1, wherein the method for adjusting the passive clearance throttling and pressure reduction comprises the following steps:
the thermal expansion coefficient of the engine stator material is selected to be smaller than that of the engine rotor material, so that the clearance value between the engine rotor and the engine stator in work is reduced, and the axial force of the rotor adjusted by local disc cavity pressure is reduced.
3. The method for adjusting the axial force of the aircraft engine rotor according to claim 1, wherein the method for adjusting the disk surface pumping pressure comprises the following steps:
set up isolation structure near engine turntable surface position, divide the carousel chamber into 2 independent cavitys, each independent cavity carries out independent exhaust respectively, carries out the local step-down that bleeds to the position that is close to engine turntable to reduce this position dish chamber axial force of carousel chamber quotation partial pressure reduction.
4. The aircraft engine rotor axial force adjustment method according to claim 1, wherein the power compensation adjustment method comprises:
designing an energy storage device, wherein one end of the energy storage device is connected with an aircraft engine, and the other end of the energy storage device is connected with an aircraft accessory or an engine accessory;
when the axial force of the engine rotor meets the design requirement, the engine rotor stores the input power of the energy storage device through power extraction;
when the axial force of the engine rotor is smaller than the minimum threshold value of the axial force, and simultaneously when the meshing force and the axial force are in the same direction, the energy storage device inputs work through the gear, and the meshing force is increased to increase the axial force; or when the meshing force is opposite to the axial force, the energy storage device outputs power to the airplane accessory, and at the moment, the power is not extracted by the engine any more so as to increase the axial force;
when the axial force of the engine rotor is larger than the maximum threshold value of the axial force, and simultaneously when the meshing force and the axial force are in the same direction, the energy storage device outputs power to the airplane accessory, and at the moment, the engine does not extract power to reduce the axial force; or when the meshing force is opposite to the axial force, the energy storage device inputs work to the gear, and the meshing force is increased to achieve the purpose of reducing the axial force.
5. The aircraft engine rotor axial force adjusting method according to any one of claims 1 to 4, wherein in the step S2, the axial force adjusting measure further comprises one or more of measures of increasing the area of a grate, adjusting the mechanical adjustable area, adding a bleed air pressurization flow path, exhausting and releasing pressure, a variable throttling unit and adjusting the direction of meshing force.
6. The aircraft engine rotor axial force adjustment method according to claim 5, wherein the aircraft engine rotor axial force adjustment method further comprises a step S5 of verifying and evaluating the adjusted engine axial force.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211256133.6A CN115680902B (en) | 2022-10-13 | 2022-10-13 | Method for adjusting axial force of aero-engine rotor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211256133.6A CN115680902B (en) | 2022-10-13 | 2022-10-13 | Method for adjusting axial force of aero-engine rotor |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN115680902A true CN115680902A (en) | 2023-02-03 |
| CN115680902B CN115680902B (en) | 2024-05-03 |
Family
ID=85065591
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211256133.6A Active CN115680902B (en) | 2022-10-13 | 2022-10-13 | Method for adjusting axial force of aero-engine rotor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115680902B (en) |
Citations (19)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH116776A (en) * | 1997-06-17 | 1999-01-12 | Honda Motor Co Ltd | Method for estimating tire lateral force |
| WO2005090781A1 (en) * | 2004-03-22 | 2005-09-29 | Sway As | A method for reduction of axial power variations of a wind power plant |
| KR20070063145A (en) * | 2005-12-14 | 2007-06-19 | 현대자동차주식회사 | A thrust force control device of injector for vehicles |
| CN101640446A (en) * | 2009-09-09 | 2010-02-03 | 北京航空航天大学 | Axial load resistant no-return-difference torque output ball-hinged driving mechanism |
| JP2012157963A (en) * | 2011-02-02 | 2012-08-23 | Nsk Ltd | Testing method and testing device for rotary shaft axial load measuring device |
| JP2014037775A (en) * | 2012-08-10 | 2014-02-27 | Hitachi Ltd | Design method of turbine, manufacturing method of turbine and determination method of non-stationary force acting on moving blade or like |
| CN203991782U (en) * | 2014-08-18 | 2014-12-10 | 零八一电子集团四川天源机械有限公司 | Valve retainer bar straightener |
| JP2016088476A (en) * | 2014-11-11 | 2016-05-23 | 川崎重工業株式会社 | Ship propulsion system |
| US20160265427A1 (en) * | 2015-03-13 | 2016-09-15 | Calnetix Technologies Llc | Supplemental Electromagnetic Turbocharger Actuator |
| DE102016209262A1 (en) * | 2016-05-27 | 2017-11-30 | Rolls-Royce Deutschland Ltd & Co Kg | Adjustment device and adjustment method of an axial load in an aircraft engine |
| US20180156063A1 (en) * | 2016-12-02 | 2018-06-07 | Rolls-Royce Deutschland Ltd & Co Kg | Arrangement, turbo engine and method for the recognition of a shaft breakage of a shaft |
| CN108252961A (en) * | 2017-12-28 | 2018-07-06 | 中国航发四川燃气涡轮研究院 | A kind of axial thrust balancing devices for axial flow compressor performance test |
| CN109117509A (en) * | 2018-07-16 | 2019-01-01 | 中国航发沈阳发动机研究所 | The design method of aero-engine booster cavity |
| JP2019209786A (en) * | 2018-06-01 | 2019-12-12 | 株式会社ジェイテクト | Steering control device |
| CN111766064A (en) * | 2020-07-31 | 2020-10-13 | 中国航发贵阳发动机设计研究所 | Ship-borne main shaft bearing impact test method |
| EP3974292A1 (en) * | 2020-09-28 | 2022-03-30 | Jtekt Corporation | Steering control device and steering system |
| CN114607510A (en) * | 2022-03-18 | 2022-06-10 | 中国航发沈阳发动机研究所 | Adaptive adjustment method and system for slip of aircraft engine |
| CN114692309A (en) * | 2022-04-08 | 2022-07-01 | 中国航发沈阳发动机研究所 | Real-time calculation method for axial force of low-pressure turbine rotor of aviation turbofan engine |
| CN114722532A (en) * | 2022-04-08 | 2022-07-08 | 中国航发沈阳发动机研究所 | Method for calculating axial force of fan rotor of aviation turbofan engine in real time |
-
2022
- 2022-10-13 CN CN202211256133.6A patent/CN115680902B/en active Active
Patent Citations (19)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH116776A (en) * | 1997-06-17 | 1999-01-12 | Honda Motor Co Ltd | Method for estimating tire lateral force |
| WO2005090781A1 (en) * | 2004-03-22 | 2005-09-29 | Sway As | A method for reduction of axial power variations of a wind power plant |
| KR20070063145A (en) * | 2005-12-14 | 2007-06-19 | 현대자동차주식회사 | A thrust force control device of injector for vehicles |
| CN101640446A (en) * | 2009-09-09 | 2010-02-03 | 北京航空航天大学 | Axial load resistant no-return-difference torque output ball-hinged driving mechanism |
| JP2012157963A (en) * | 2011-02-02 | 2012-08-23 | Nsk Ltd | Testing method and testing device for rotary shaft axial load measuring device |
| JP2014037775A (en) * | 2012-08-10 | 2014-02-27 | Hitachi Ltd | Design method of turbine, manufacturing method of turbine and determination method of non-stationary force acting on moving blade or like |
| CN203991782U (en) * | 2014-08-18 | 2014-12-10 | 零八一电子集团四川天源机械有限公司 | Valve retainer bar straightener |
| JP2016088476A (en) * | 2014-11-11 | 2016-05-23 | 川崎重工業株式会社 | Ship propulsion system |
| US20160265427A1 (en) * | 2015-03-13 | 2016-09-15 | Calnetix Technologies Llc | Supplemental Electromagnetic Turbocharger Actuator |
| DE102016209262A1 (en) * | 2016-05-27 | 2017-11-30 | Rolls-Royce Deutschland Ltd & Co Kg | Adjustment device and adjustment method of an axial load in an aircraft engine |
| US20180156063A1 (en) * | 2016-12-02 | 2018-06-07 | Rolls-Royce Deutschland Ltd & Co Kg | Arrangement, turbo engine and method for the recognition of a shaft breakage of a shaft |
| CN108252961A (en) * | 2017-12-28 | 2018-07-06 | 中国航发四川燃气涡轮研究院 | A kind of axial thrust balancing devices for axial flow compressor performance test |
| JP2019209786A (en) * | 2018-06-01 | 2019-12-12 | 株式会社ジェイテクト | Steering control device |
| CN109117509A (en) * | 2018-07-16 | 2019-01-01 | 中国航发沈阳发动机研究所 | The design method of aero-engine booster cavity |
| CN111766064A (en) * | 2020-07-31 | 2020-10-13 | 中国航发贵阳发动机设计研究所 | Ship-borne main shaft bearing impact test method |
| EP3974292A1 (en) * | 2020-09-28 | 2022-03-30 | Jtekt Corporation | Steering control device and steering system |
| CN114607510A (en) * | 2022-03-18 | 2022-06-10 | 中国航发沈阳发动机研究所 | Adaptive adjustment method and system for slip of aircraft engine |
| CN114692309A (en) * | 2022-04-08 | 2022-07-01 | 中国航发沈阳发动机研究所 | Real-time calculation method for axial force of low-pressure turbine rotor of aviation turbofan engine |
| CN114722532A (en) * | 2022-04-08 | 2022-07-08 | 中国航发沈阳发动机研究所 | Method for calculating axial force of fan rotor of aviation turbofan engine in real time |
Non-Patent Citations (7)
| Title |
|---|
| XUE, Y AND GE, N: "Engineering Application of an Identification Method to Shock-Induced Vortex Stability in the Transonic Axial Fan Rotor", INTERNATIONAL JOURNAL OF AEROSPACE ENGINEERING, 21 July 2021 (2021-07-21), pages 1 - 24 * |
| 刘志刚;曾军;赵旺东;刘宪;谢金伟;: "全尺寸对转涡轮若干关键试验技术的应用验证", 燃气涡轮试验与研究, no. 01, 15 February 2017 (2017-02-15), pages 1 - 6 * |
| 张海磊;王强;任洋;何嘉伟;靳嵘: "车用涡轮增压器轴向气动作用力分析", 机床与液压, 28 May 2019 (2019-05-28), pages 77 - 81 * |
| 林磊;伏宇;: "航空发动机滚珠轴承轴向载荷的间接测量方法", 燃气涡轮试验与研究, no. 03, 31 August 2011 (2011-08-31), pages 38 - 40 * |
| 王秋阳;陈亮;: "航空发动机转子气体轴向力技术研究", 中国设备工程, no. 07, 10 April 2018 (2018-04-10), pages 179 - 182 * |
| 王鉴; 王春雷; 万玉倩: "运用摩擦学原理改进水轮机主轴密封装置的设计", 人民长江, 14 January 2013 (2013-01-14), pages 69 - 73 * |
| 蔡毅;朱惠人;张丽;王永杰;: "影响某型燃机转子轴向力关键因素分析", 航空工程进展, no. 01, 28 February 2013 (2013-02-28), pages 66 - 70 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN115680902B (en) | 2024-05-03 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| EP2388672B1 (en) | Identifying of turbomachine faults | |
| Verstraete | Multidisciplinary turbomachinery component optimization considering performance, stress, and internal heat transfer | |
| Hall et al. | Performance limits of axial compressor stages | |
| Wellborn et al. | Redesign of a 12-stage axial-flow compressor using multistage CFD | |
| GB2462922A (en) | Method for reducing the vibration levels of a propeller of a turbine engine | |
| CN112347570B (en) | Air system design method | |
| Buske et al. | Distributed multidisciplinary optimization of a turbine blade regarding performance, reliability and castability | |
| CN113486561B (en) | Engine rotor dynamic characteristic improving method based on strain energy distribution | |
| CN115680902A (en) | Method for adjusting axial force of rotor of aircraft engine | |
| Ning et al. | Blade forced response prediction for industrial gas turbines: Part 2—verification and application | |
| Gorrell et al. | Upstream wake influences on the measured performance of a transonic compressor stage | |
| CN112069616A (en) | Intelligent service life prolonging control method for recycling of retired aircraft engine | |
| CN117010099A (en) | High-low pressure turbine matching design method for cross-generation small-bypass-ratio turbofan engine | |
| CN115659433B (en) | Quantitative evaluation method for mechanical characteristics of aero-engine rotor structure | |
| CN115356119A (en) | Design method of low-cycle fatigue life test scheme of multistage low-pressure turbine rotor | |
| Ke et al. | Highly loaded aerodynamic design and three dimensional performance enhancement of a HTGR helium compressor | |
| CN115406664A (en) | Method and system for compiling turbo-propeller engine acceleration task trial spectrum | |
| US8375698B2 (en) | Method for reducing the vibration levels of a propfan of contrarotating bladed disks of a turbine engine | |
| CN114739682A (en) | High cycle fatigue test design method for aviation turbojet and turbofan engine | |
| CN111814370A (en) | Finite element calculation method for adjusting-stage blade | |
| Li et al. | Prediction of rotor burst using strain-based fracture criteria to comply with the engine airworthiness regulation | |
| CN115753121B (en) | Engine core machine durability verification method | |
| Benvenuti | Design and test of a new axial compressor for the Nuovo Pignone Heavy-Duty gas turbines | |
| Brunn et al. | Improved LP-Stage Design for Industrial Steam Turbines | |
| CN115355193B (en) | Dynamic regulation and control method for axial force of gas compressor under heating and pressurizing conditions |
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 |