CN102589889A - Overall-unit forced surge method for engine - Google Patents
Overall-unit forced surge method for engine Download PDFInfo
- Publication number
- CN102589889A CN102589889A CN2012100409442A CN201210040944A CN102589889A CN 102589889 A CN102589889 A CN 102589889A CN 2012100409442 A CN2012100409442 A CN 2012100409442A CN 201210040944 A CN201210040944 A CN 201210040944A CN 102589889 A CN102589889 A CN 102589889A
- Authority
- CN
- China
- Prior art keywords
- engine
- surge
- forced
- margin
- complete machine
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Images
Landscapes
- Control Of Positive-Displacement Air Blowers (AREA)
Abstract
The invention provides an overall-unit forced surge method for an engine, which successively comprises the following steps: 1. providing a gas compressor, and obtaining a surge margin of the gas compressor; 2. starting the engine, introducing high-pressure gas into the engine so that the engine approaches to the surge margin, and meanwhile, collecting the parameters of the engine by a surge monitor in real time; and 3. according to the parameters obtained by the surge monitor, determining the surge allowance of the engine. With the overall-unit forced surge method for the engine, the surge allowance and the pneumatic stability of the engine can be accurately determined. The method comprises simple operation steps, and the test risk is greatly lowered.
Description
Technical field
The present invention relates to the aeromotor field, especially, the complete machine that relates to a kind of engine is forced and is breathed heavily method.
Background technology
The shaft gas turbine engine complete machine forces the technology of breathing heavily mainly the aerodynamic stability of engine to be verified.Whether the aerodynamic stability of engine meets the demands, and mainly confirms through the complete machine surge margin of detection of engine.
At present, mainly adopt the method for fuel oil step to make engine get into surge, thereby obtain the surge margin of engine.Adopt the method for fuel oil step need carry out test of many times, confirming to cause the fuel oil step amount of engine surge, and the fuel oil step amount should not be controlled.In addition; Owing to increase one bigger fuel flow to engine in the short time at the utmost point; In-engine fuel gas temperature sharply rises at short notice; Cause problems such as blade ablation, fracture, rotating speed fluctuation easily, possibly cause the mechanical damage of engine and other equipment, empirical risk is bigger.
Know by above, adopt the method complicated operation of fuel oil step, and empirical risk is bigger.
Summary of the invention
The object of the invention is to provide a kind of complete machine of engine to force to breathe heavily method, to solve the bigger technical matters of method complicated operation, empirical risk of prior fuel oil step.
Be to realize above-mentioned purpose, according to an aspect of the present invention, provide a kind of complete machine of engine to force and breathed heavily method that this method in turn includes the following steps: the first step: a pneumatic plant is provided, and obtains the stall margin of pneumatic plant; Second step: starting engine, and gases at high pressure are introduced in the engine, make engine approach the stall margin, simultaneously, the parameter of using the surge monitor to gather engine in real time; The 3rd step: the parameter that obtains according to the surge monitor is confirmed the surge margin of engine.
Further, in the first step, pneumatic plant experimentizes at the component test platform, obtains the stall margin.
Further, in second step, also provide to force and breathe heavily test unit, outside gases at high pressure are breathed heavily test unit and are introduced in the engine through the outlet of pneumatic plant through forcing.
Further, in second step, the surge monitor is gathered the parameter that engine is in surging condition in real time.
Further, after the 3rd step, according to the aerodynamic stability of surge margin assessment engine.
The present invention has following beneficial effect: adopt the complete machine of engine of the present invention to force and breathe heavily method, can confirm the surge margin and the aerodynamic stability of engine exactly, and the operation steps of this method is simple, empirical risk reduces greatly.
Except top described purpose, feature and advantage, the present invention also has other purpose, feature and advantage.To do further detailed explanation to the present invention with reference to figure below.
Description of drawings
The accompanying drawing that constitutes the application's a part is used to provide further understanding of the present invention, and illustrative examples of the present invention and explanation thereof are used to explain the present invention, do not constitute improper qualification of the present invention.In the accompanying drawings:
Fig. 1 is that the complete machine of the engine of the preferred embodiment of the present invention is forced the schematic flow sheet of breathing heavily method.
Embodiment
Below in conjunction with accompanying drawing embodiments of the invention are elaborated, but the multitude of different ways that the present invention can be defined by the claims and cover is implemented.
Referring to Fig. 1, the complete machine of engine of the present invention is forced and is breathed heavily method and comprise the steps:
Step S01 provides a pneumatic plant, and obtains the stall margin of this pneumatic plant.Preferably, elder generation experimentizes pneumatic plant on the component test platform, thereby obtains the stall margin of this pneumatic plant.Then carry out step S02.
Step S02, starting engine, and gases at high pressure are introduced in the engine, make engine progressively approach the stall margin, and use the surge monitor to gather the parameter of engine in real time simultaneously.
In step S02, the device and of input gases at high pressure is forced and is breathed heavily test unit and be connected, and forces to breathe heavily test unit and be connected with the outlet of pneumatic plant, and the outlet of pneumatic plant and the inner chamber of engine connect.During use; The gases at high pressure of importing from the outside are breathed heavily test unit through special-purpose forcing earlier and are controlled; Gases at high pressure through after the control are introduced in the engine from the outlet of pneumatic plant again, thereby make the engine in the work progressively approach the stall margin that in step S01, is obtained.
And; Progressively approach in the process of stall margin at engine; Preferably, adopt high frequency sound, high-precision surge monitor to gather intake air flow, the static pressure on the water conservancy diversion basin, blower outlet stagnation pressure and static pressure, compressor inlet static pressure and the parameters such as stagnation pressure and fuel flow that engine is in surging condition in real time.Then carry out following steps S03.
Step S03, the parameter that obtains according to the surge monitor, thus confirm the surge margin of engine.
In step S03, the surge margin of engine in whole work envelope curve is not less than 13%, to reach the design objective of engine.
Behind step S03, for the aerodynamic stability of understanding engine how, can come the accurately aerodynamic stability of assessment engine according to the surge margin of confirming.
Adopt the complete machine of engine of the present invention to force and breathe heavily method, can confirm the surge margin and the aerodynamic stability of engine exactly, and the operation steps of this method is simple, empirical risk reduces greatly.
The above is merely the preferred embodiments of the present invention, is not limited to the present invention, and for a person skilled in the art, the present invention can have various changes and variation.All within spirit of the present invention and principle, any modification of being done, be equal to replacement, improvement etc., all should be included within protection scope of the present invention.
Claims (5)
1. the complete machine of an engine is forced and is breathed heavily method, it is characterized in that, said method in turn includes the following steps:
The first step a: pneumatic plant is provided, and obtains the stall margin of said pneumatic plant;
Second step: starting engine, and gases at high pressure are introduced in the said engine, make said engine approach said stall margin, simultaneously, use the surge monitor to gather the parameter of said engine in real time;
The 3rd step: the said parameter that obtains according to said surge monitor is confirmed the surge margin of said engine.
2. the complete machine of engine according to claim 1 is forced and is breathed heavily method, it is characterized in that, in the said first step, said pneumatic plant experimentizes at the component test platform, obtains said stall margin.
3. the complete machine of engine according to claim 1 is forced and is breathed heavily method; It is characterized in that; In said second step, also provide to force and breathe heavily test unit, outside said gases at high pressure are breathed heavily test unit and are introduced in the said engine through the outlet of said pneumatic plant through said forcing.
4. the complete machine of engine according to claim 1 is forced and is breathed heavily method, it is characterized in that, in said second step, said surge monitor is gathered the said parameter that said engine is in surging condition in real time.
5. the complete machine of engine according to claim 1 is forced and is breathed heavily method, it is characterized in that, after said the 3rd step, assesses the aerodynamic stability of said engine according to said surge margin.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012100409442A CN102589889A (en) | 2012-02-23 | 2012-02-23 | Overall-unit forced surge method for engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012100409442A CN102589889A (en) | 2012-02-23 | 2012-02-23 | Overall-unit forced surge method for engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN102589889A true CN102589889A (en) | 2012-07-18 |
Family
ID=46478835
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2012100409442A Pending CN102589889A (en) | 2012-02-23 | 2012-02-23 | Overall-unit forced surge method for engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102589889A (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103852119A (en) * | 2014-03-10 | 2014-06-11 | 西北工业大学 | Continuous wind tunnel compressor inlet flow measurement method |
| CN103852234A (en) * | 2014-03-10 | 2014-06-11 | 西北工业大学 | Surge limit measurement method for continuous transonic wind tunnel |
| CN105423343A (en) * | 2014-08-28 | 2016-03-23 | 中航商用航空发动机有限责任公司 | Aero-engine combustion chamber and large-bypass-ratio turbofan engine |
| CN106323640A (en) * | 2015-06-30 | 2017-01-11 | 中航空天发动机研究院有限公司 | Acceleration and deceleration oil supply test method for aeroengines |
| CN112253523A (en) * | 2020-12-08 | 2021-01-22 | 中国航发上海商用航空发动机制造有限责任公司 | Test method and tester for identifying stall initial stage of multistage axial flow compressor |
| CN112483454A (en) * | 2020-11-12 | 2021-03-12 | 中国航发沈阳黎明航空发动机有限责任公司 | Evaluation method for surge margin of gas compressor |
| CN115184023A (en) * | 2022-06-29 | 2022-10-14 | 中国航发湖南动力机械研究所 | Auxiliary oil supply device for aero-engine surge test and adjusting method thereof |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20060045772A1 (en) * | 2004-08-31 | 2006-03-02 | Slovisky John A | Compressor including an aerodynamically variable diffuser |
| US20090112490A1 (en) * | 2007-10-09 | 2009-04-30 | Eric Matlis | Plasma sensors and related methods |
| CN201247151Y (en) * | 2008-08-22 | 2009-05-27 | 中国航空动力机械研究所 | Automatic control device for engine experimental axial force |
-
2012
- 2012-02-23 CN CN2012100409442A patent/CN102589889A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20060045772A1 (en) * | 2004-08-31 | 2006-03-02 | Slovisky John A | Compressor including an aerodynamically variable diffuser |
| US20090112490A1 (en) * | 2007-10-09 | 2009-04-30 | Eric Matlis | Plasma sensors and related methods |
| CN201247151Y (en) * | 2008-08-22 | 2009-05-27 | 中国航空动力机械研究所 | Automatic control device for engine experimental axial force |
Non-Patent Citations (1)
| Title |
|---|
| 旷桂兰等: "某涡轴发动机整机逼喘试验研究", 《航空动力学报》, vol. 24, no. 3, 31 March 2009 (2009-03-31), pages 588 - 595 * |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103852119A (en) * | 2014-03-10 | 2014-06-11 | 西北工业大学 | Continuous wind tunnel compressor inlet flow measurement method |
| CN103852234A (en) * | 2014-03-10 | 2014-06-11 | 西北工业大学 | Surge limit measurement method for continuous transonic wind tunnel |
| CN105423343A (en) * | 2014-08-28 | 2016-03-23 | 中航商用航空发动机有限责任公司 | Aero-engine combustion chamber and large-bypass-ratio turbofan engine |
| CN105423343B (en) * | 2014-08-28 | 2017-12-29 | 中国航发商用航空发动机有限责任公司 | Aeroengine combustor buring room and big Bypass Ratio Turbofan Engine |
| CN106323640A (en) * | 2015-06-30 | 2017-01-11 | 中航空天发动机研究院有限公司 | Acceleration and deceleration oil supply test method for aeroengines |
| CN112483454A (en) * | 2020-11-12 | 2021-03-12 | 中国航发沈阳黎明航空发动机有限责任公司 | Evaluation method for surge margin of gas compressor |
| CN112483454B (en) * | 2020-11-12 | 2022-03-04 | 中国航发沈阳黎明航空发动机有限责任公司 | Evaluation method for surge margin of gas compressor |
| CN112253523A (en) * | 2020-12-08 | 2021-01-22 | 中国航发上海商用航空发动机制造有限责任公司 | Test method and tester for identifying stall initial stage of multistage axial flow compressor |
| CN115184023A (en) * | 2022-06-29 | 2022-10-14 | 中国航发湖南动力机械研究所 | Auxiliary oil supply device for aero-engine surge test and adjusting method thereof |
| CN115184023B (en) * | 2022-06-29 | 2024-09-27 | 中国航发湖南动力机械研究所 | Auxiliary oil supply device for aero-engine surge test and adjusting method thereof |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102589889A (en) | Overall-unit forced surge method for engine | |
| CN110717219B (en) | Method and device for acquiring inlet flow of air compressor in complete machine state of aero-engine | |
| US6935119B2 (en) | Methods for operating gas turbine engines | |
| CN104481601B (en) | The crack propagation service life supervision method of turbine rotor low cycle fatigue and high cycle fatigue | |
| EP3131025A1 (en) | Method for the prediction of surge in a gas compressor | |
| EP2375005A3 (en) | Method for controlling turbine blade tip seal clearance | |
| CN102734149B (en) | Compressor performance testing system | |
| CN1908381A (en) | Online computing and controlling method for steam turbine high and medium pressure rotator equivalent stress | |
| EP1691055A3 (en) | Intercooling in gas turbine engines | |
| CN104408243B (en) | A kind of engine mockup installed thrust modification method | |
| CN113482960B (en) | Method for judging surge of aviation gas turbine engine | |
| CN107407618A (en) | Purposes for the device of regulation air, method and described device when testing reciprocating internal combustion engine | |
| EP2354449A3 (en) | Method and apparatus for double flow turbine first stage cooling | |
| Li et al. | Numerical and experimental research on different inlet configurations of high speed centrifugal compressor | |
| CN101900655B (en) | Rupture disk fatigue tester for 400MPa gas cylinders | |
| CN102505969A (en) | Device for monitoring service lives of valve casing of steam turbine and crack propagations of cylinder and method | |
| CN111046490B (en) | Grid size inversion method in foreign object damage notch analysis | |
| CN103558016B (en) | Full working scope seal test device | |
| EP1793089A3 (en) | Method and apparatus for reducing axial compressor blade tip flow | |
| CN206919311U (en) | A kind of prefabricated pumping plant forces air draft integrated system | |
| CN205620024U (en) | Air conditioner pipeline vibration test system | |
| CN205136057U (en) | Large -scale centrifugal pump comprehensive properties testing arrangement | |
| CN103852234A (en) | Surge limit measurement method for continuous transonic wind tunnel | |
| CN106018149A (en) | Visual cylinder liner cavitation erosion test device and method | |
| EP2551455A3 (en) | Master component for flow calibration |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C12 | Rejection of a patent application after its publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20120718 |