CN104515683A - Engine power margin and heat margin examining method for two-engine helicopter - Google Patents
Engine power margin and heat margin examining method for two-engine helicopter Download PDFInfo
- Publication number
- CN104515683A CN104515683A CN201310460171.8A CN201310460171A CN104515683A CN 104515683 A CN104515683 A CN 104515683A CN 201310460171 A CN201310460171 A CN 201310460171A CN 104515683 A CN104515683 A CN 104515683A
- Authority
- CN
- China
- Prior art keywords
- engine
- power
- inspection
- nargin
- torque
- 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
- 238000000034 method Methods 0.000 title claims abstract description 37
- 238000012544 monitoring process Methods 0.000 claims abstract description 22
- 238000007689 inspection Methods 0.000 claims description 47
- 238000001514 detection method Methods 0.000 claims description 3
- 238000012423 maintenance Methods 0.000 description 2
- 208000019901 Anxiety disease Diseases 0.000 description 1
- 230000036506 anxiety Effects 0.000 description 1
- 230000004888 barrier function Effects 0.000 description 1
- FFBHFFJDDLITSX-UHFFFAOYSA-N benzyl N-[2-hydroxy-4-(3-oxomorpholin-4-yl)phenyl]carbamate Chemical compound OC1=C(NC(=O)OCC2=CC=CC=C2)C=CC(=C1)N1CCOCC1=O FFBHFFJDDLITSX-UHFFFAOYSA-N 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 102220062467 rs745423387 Human genes 0.000 description 1
- GOLXNESZZPUPJE-UHFFFAOYSA-N spiromesifen Chemical compound CC1=CC(C)=CC(C)=C1C(C(O1)=O)=C(OC(=O)CC(C)(C)C)C11CCCC1 GOLXNESZZPUPJE-UHFFFAOYSA-N 0.000 description 1
Landscapes
- Testing Of Engines (AREA)
Abstract
本发明属于发动机控制系统，本发明提供一种双发直升机的发动机功率裕度和热裕度检查方法，包括：在飞行状态下，当用户选择对两台发动机中的一台进行检查时，保持当前两台发动机输出的总功率或者总扭矩不变，提高被检发动机功率或者扭矩或燃气发生器涡轮转速到被检发动机监控参数目标值，同时降低备检发动机功率或者扭矩或燃气发生器涡轮转速到备检发动机监控参数目标值。
The invention belongs to an engine control system. The invention provides a method for checking engine power margin and thermal margin of a twin-engine helicopter. The total output power or total torque of the current two engines remains unchanged, increase the power or torque of the checked engine or the speed of the gas generator turbine to the target value of the monitoring parameter of the checked engine, and at the same time reduce the power or torque of the standby engine or the speed of the gas generator turbine to the target value of the monitoring parameter of the standby engine.
Description
Technical field
The invention belongs to engine control system, relate to a kind of engine capacity nargin of two helicopters and hot nargin inspection method.
Background technology
For two helicopters, judge that the most important monitoring parameter of engine performance index is turbine inlet temperature (TIT) TET and power W.A lot of engine reflects TET indirectly by measuring free turbine inlet temperature T45.The engine of modern helicopters regularly need carry out power margin and hot nargin inspection, usually to determine the power margin of engine and hot nargin, with the performance change of monitoring engine and fault.
According to the power allocation case classification of two engines in engine capacity nargin and the inspection of hot nargin, existing engine capacity nargin and hot nargin inspection can be divided into three kinds of methods.
First method, in helicopter cruising flight, two engine capacitys are equal, carry out engine capacity nargin and hot nargin inspection.The advantage of this method can check in normal flight, do not affect the execution of task.But this method exists significant shortcoming, and namely now engine capacity is lower, under this power, carry out engine capacity nargin and hot nargin check result is inaccurate.Further, this method inspection do not go out engine whether can reach emergency rating under minimum guaranteed output.When carrying out engine capacity nargin and the inspection of hot nargin, should check with the power as far as possible close to emergency rating, should carry out under take-off power for two helicopters.But can not take-off power be reached in cruising flight.
Second method, helicopter flies with maximum continuous state, and two engine capacitys are equal, carries out engine capacity nargin and hot nargin inspection.The advantage of this method is, can check at larger power, thus check result is comparatively accurate.But in this state, the speed of helicopter is comparatively large, and vibration & noise is strong, thus may cause being discontented with of passenger.Further, usually need to improve flying height and helicopter weight, make helicopter power increase to close to take-off power, this just may need to arrange aerial mission to carry out power margin and hot nargin inspection specially.
The third method, make an engine capacity be reduced to zero, another engine is increased to take-off power.As long as the advantage of this method controls proper, one reaches take-off power surely, and therefore check result is comparatively accurate.This method can realize by hand control helicopter, also can be realized by automaton, implement fairly simple, the shortcoming of this method is that single-engine flight has certain risk, once examined power failure, namely two engines lose power, before another engine accelerates and provides enough power, helicopter will enter autorotative glide, if helicopter height is lower or have the situations such as barrier, by critical flight safety.In addition, modern helicopters generally all has power loss detection system, when two engine monitoring parameters (power W, moment of torsion C or gas generator secondary speed Ng) difference exceeds certain numerical value, helicopter can detect power loss, and send red alarm signal, notify that pilot carries out landing and even force-land.Check according to the third method, then can cause occurring this red alarm situation, in the case, pilot must ignore these red alarm signals, and performing a series of operation at the appointed time, this will seriously increase the working load of pilot, in the process, easily causing occurring faulty operation, is harmful to the safety of flight safety and engine.In view of the foregoing, helicopter has and according to said method carry out engine capacity nargin when passenger and hot nargin inspection is unsuitable.Special aerial mission must be arranged to check.
The engine of modern helicopters requires within every 20 hours ~ 25 hours, to carry out power margin and heat inspection usually.Therefore, arrange special aerial mission to check, be a significant increase the maintenance cost of helicopter, and, reduce the task attendance time of helicopter.
Summary of the invention
Object of the present invention: propose a kind of engine capacity nargin of two helicopters and hot nargin inspection method, crew is enable not need special flight, do not affect helicopter when normally executing the task, complete engine capacity nargin and hot nargin inspection accurately and effectively.
Technical scheme of the present invention: a kind of engine capacity nargin of two helicopters and hot nargin inspection method, comprising:
Under state of flight, when user selects to check in two engines, the general power keeping current two engines to export or total torque constant, improve tested engine capacity or moment of torsion or gas generator secondary speed to tested engine monitoring parameter objectives value, reduce standby inspection engine capacity or moment of torsion or gas generator secondary speed to standby inspection engine monitoring parameter objectives value simultaneously.
Advantage of the present invention: adopt engine capacity nargin of the present invention and hot nargin inspection method, crew can be enable not need special flight, do not affect helicopter when normally executing the task, complete engine capacity nargin and hot nargin inspection accurately and effectively.
Accompanying drawing illustrates:
Fig. 1 is the structural representation of a kind of device realizing the method for the invention.
Embodiment:
Below in conjunction with accompanying drawing, the present invention is described in further detail.
The engine capacity nargin of a kind of two helicopters of the present invention and hot nargin inspection method, comprising:
S101, under state of flight, when user selects to check in two engines, the general power keeping current two engines to export or total torque constant, improve tested engine capacity or moment of torsion or gas generator secondary speed to tested engine monitoring parameter objectives value, reduce standby inspection engine capacity or moment of torsion or gas generator secondary speed to standby inspection engine monitoring parameter objectives value simultaneously.
S102, alarm limits difference is set, when user selects to check in two engines, if the power that tested engine examines engine with standby or moment of torsion or gas generator secondary speed desired value difference can reach described alarm limits difference, then forbid that user detects, and the general power pointing out user to allow to carry out detecting required two engines output or moment of torsion.
S103, check after, before tested engine and standby inspection engine capacity or moment of torsion or gas generator secondary speed return to inspection.
Be further described with embodiment 1 couple of the present invention below:
Embodiment 1
As shown in Figure 1, two helicopters have two engines, 1(engine 1) and 2(engine 2), they are respectively by the electronic controller of 3(engine 1) and the electronic controller of 4(engine 2) control.Helicopter has a 5(power margin and hot nargin inspection control enclosure) for carrying out power margin and hot nargin inspection.5 comprise 6(primary module), 7(parameter acquisition and output display module) and 8(computing module).8 also can be included in 3 and 4.
6 for resetting the DifPM(alarm limits value of engine), determine the monitoring parameter P of in power margin and hot nargin checking process 1 and 2
m1and P
m2desired value P
m1 targetand P
m2 target, and by controlling 3 and 4 to control 1 and 2, make P
m1and P
m2reach P
m1 targetand P
m2 target.
7 for the collection of 1 and 2 parameters and the output display of result of calculation before power margin and the inspection of hot nargin and in checking process.
8 for the calculating of power margin and hot nargin.
Before power margin and hot nargin check, the power of 1 and 2 is respectively W
1and W
2, power and be W
1+2, in power margin and hot nargin checking process, reach W respectively at the power of 1 and 2
1 targetand W
2 targets.
If do not meet inspection condition, calculate and inform the numerical value P that crew's monitoring parameter should reach
m'.
The power margin calculated is △ W, and hot nargin is △ T45.
Cockpit crew selects to perform power margins and hot nargin inspection (such as by modes such as the switch that arranges on 5 or buttons) to 1 or 2 by 5, and helicopter automatically performs the following step:
A. alarm limits difference Dif between two engines is reset by 5
pM, such as, when normally working, alarm limits value is that two Ng of sending out differs 3%(Dif
pM=3%), alarm limits value when carrying out power margin and the inspection of hot nargin is adjusted to Dif
pM=5%.
B. obtain the parameter checking front two engines, calculate two power W(or moments of torsion) sum W
1+2, such as, before checking W
1=800kw, W
2=810kw, other parameters are omited, W
1+2=1620kw.
C. the monitoring parameter desired value P that examined engine will reach in checking process is determined
m1 target, such as Ng
1 target=98%, this parameter corresponds to the Ng value of take-off power state under local atmospheric conditions (comprising temperature, pressure etc.).
D. the monitoring parameter desired value P that standby inspection engine will reach in checking process is determined
m2 order mark, such as Ng
2 targets=93.5%, now W
1 target+ W2
target=1100kw+520kw=1620kw=W
1+2.
If e. tested engine target value is less than with the standby difference examining engine target value the alarm limits difference arranged according to a., so perform g. bar.Such as Ng
1 target-Ng
2 targets=98%-93.5%=4.5%<Dif
ng, satisfy condition, perform g. bar.
Such as, if f. tested engine target value exceedes the alarm limits difference arranged according to a., the Ng calculated in d. with the standby difference examining engine target value
2 targets==92%, then Ng
1 target-Ng
2 target=98%-92%=6%>Dif
ng, then notify that Pilot Check's condition does not meet the demands, and inform the pilot numerical value P that monitoring parameter should reach when carrying out power and checking
m', such as W
1+294% ~ 96% should be should be at 1800 ~ 1900kw(or two Ng, and end check program.At this moment, pilot can improve the methods such as flying speed and reach inspection requirements, and then performs inspection.
G. control examined engine, this engine monitoring parameter is increased, in checking process, reaches tested engine target value.Control standby inspection engine, this engine monitoring parameter is declined, in checking process, reach standby inspection engine target value, such as Ng1=98%, Ng2=93.5%.
H., when two engine monitoring parameters reach respective desired value and stablize, several groups of parameters of engine are obtained.
I. engine capacity nargin and the calculating of hot nargin is carried out, and output engine power margin and hot nargin result.Such as △ W=+50kw and △ T45=+35 DEG C, both be all on the occasion of, show that engine performance is normal.
J. end check program: control examined engine, this engine monitoring parameter is reduced, turn back to state before checking, controls standby inspection engine, this engine monitoring parameter is increased, turns back to state before checking.Such as, W1=800kw, W2=810kw, other parameters slightly.
As can be seen from above-mentioned execution step, the method of the invention comprises the alarm limits difference reset between two engines, determine tested engine target value and standby inspection engine target value, control engine and reach respective value, carry out power margin and hot nargin calculating etc.
When implementing this method, the monitoring parameter of engine can be power (or moment of torsion), also can be engine gas generator secondary speed, etc.
When crew selects to perform engine capacity nargin and the inspection of hot nargin, by resetting the alarm limits value of engine, ensure that power (or moment of torsion, the gas generator secondary speed) difference between two engines does not exceed alarm limits value, effectively avoid red alarm signal.Pass through control module, the power division of adjustment two engines, an engine capacity is made to reduce (but still having certain power), another engine capacity is increased to take-off power (also can be other power ratings that engine producer is agreed to), and the power sum of two engines is remained unchanged before and after power margin and hot nargin inspection.
Adopt engine capacity nargin of the present invention and hot nargin inspection method, crew can be enable not need special flight, do not affect helicopter when normally executing the task, complete engine capacity nargin and hot nargin inspection accurately and effectively.
Adopt engine capacity nargin of the present invention and hot nargin inspection method, because two power sums remain unchanged, go straight up to function and maintain original attitude, reset alarm limits value, can avoid occurring the red alarm situation of engine, therefore pilot is not needed to carry out unnecessary manipulation, pilot's anxiety and emergency disposal can not be caused, thus crew can be enable not need special flight, do not affect helicopter when normally executing the task, perform engine capacity nargin and hot nargin inspection.Safety for flight safety and engine is very favorable, effectively can reduce maintenance work simultaneously, cut operating costs.
And, because an engine can reach take-off power, accurate believable engine capacity nargin and hot nargin check result can be obtained.Another engine still maintains certain power, loses power once examined power failure, and standby inspection engine can accelerate very soon and provide power, dangerous situation can be avoided to occur, improves the security of helicopter.
Claims (3)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310460171.8A CN104515683A (en) | 2013-09-30 | 2013-09-30 | Engine power margin and heat margin examining method for two-engine helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310460171.8A CN104515683A (en) | 2013-09-30 | 2013-09-30 | Engine power margin and heat margin examining method for two-engine helicopter |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104515683A true CN104515683A (en) | 2015-04-15 |
Family
ID=52791314
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310460171.8A Pending CN104515683A (en) | 2013-09-30 | 2013-09-30 | Engine power margin and heat margin examining method for two-engine helicopter |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104515683A (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110621858A (en) * | 2017-04-03 | 2019-12-27 | 赛峰直升机发动机公司 | Method for checking the maximum available power of a turbine engine of an aircraft equipped with two turbine engines |
| CN110803297A (en) * | 2019-10-18 | 2020-02-18 | 哈尔滨飞机工业集团有限责任公司 | Airworthiness test method for single-shot performance of CCAR29 helicopters |
| CN112173169A (en) * | 2020-09-25 | 2021-01-05 | 中国直升机设计研究所 | Automatic checking method for engine power of three-engine helicopter |
| CN112197974A (en) * | 2020-09-25 | 2021-01-08 | 中国直升机设计研究所 | Simplified display method for three-engine helicopter engine parameters |
| US11427353B2 (en) | 2019-12-13 | 2022-08-30 | Pratt & Whitney Canada Corp. | System and method for testing engine performance in-flight |
| CN117516952A (en) * | 2023-11-09 | 2024-02-06 | 中国航发湖南动力机械研究所 | Aviation gas turbine shaft engine power guarantee inspection method |
-
2013
- 2013-09-30 CN CN201310460171.8A patent/CN104515683A/en active Pending
Non-Patent Citations (1)
| Title |
|---|
| 林达锦 等: "基于功率裕度的某型发动机全寿命性能研究", 《中国民航大学学报》 * |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110621858A (en) * | 2017-04-03 | 2019-12-27 | 赛峰直升机发动机公司 | Method for checking the maximum available power of a turbine engine of an aircraft equipped with two turbine engines |
| CN110621858B (en) * | 2017-04-03 | 2022-02-08 | 赛峰直升机发动机公司 | Method for checking the maximum available power of a turbine engine of an aircraft equipped with two turbine engines |
| CN110803297A (en) * | 2019-10-18 | 2020-02-18 | 哈尔滨飞机工业集团有限责任公司 | Airworthiness test method for single-shot performance of CCAR29 helicopters |
| US11427353B2 (en) | 2019-12-13 | 2022-08-30 | Pratt & Whitney Canada Corp. | System and method for testing engine performance in-flight |
| CN112173169A (en) * | 2020-09-25 | 2021-01-05 | 中国直升机设计研究所 | Automatic checking method for engine power of three-engine helicopter |
| CN112197974A (en) * | 2020-09-25 | 2021-01-08 | 中国直升机设计研究所 | Simplified display method for three-engine helicopter engine parameters |
| CN117516952A (en) * | 2023-11-09 | 2024-02-06 | 中国航发湖南动力机械研究所 | Aviation gas turbine shaft engine power guarantee inspection method |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104515683A (en) | Engine power margin and heat margin examining method for two-engine helicopter | |
| CN107168205B (en) | An online health monitoring data collection and analysis method for civil aircraft air conditioning system | |
| CN101055229B (en) | Method and a device for performing a check on the state of health of a turbine engine of a twin-engined rotorcraft | |
| CN107703379B (en) | System and method for monitoring critical components on an aircraft | |
| CN105741381B (en) | A kind of method that determining aircraft flies ginseng recording parameters set | |
| US9233763B1 (en) | Methods and systems for aircraft systems health trend monitoring | |
| EP3124385B1 (en) | Power safety instrument system | |
| US11459960B2 (en) | Method for checking the maximum available power of a turbine engine of an aircraft equipped with two turbine engines | |
| US11794916B2 (en) | Control systems for hybrid electric power plants | |
| EP3927620B1 (en) | Control systems for hybrid electric powerplants | |
| CN107703914A (en) | A kind of aero-engine FADEC security of system appraisal procedures | |
| CN104471502A (en) | Safe takeoff monitoring system | |
| JP6590419B2 (en) | System and method for controlling the pressure field around an aircraft in flight | |
| RU2619661C2 (en) | Gas turbine engine, containing the monitoring system containing the module of inclusion of the function of the protection of the gas turbine engine, and the method of monitoring | |
| Sherry et al. | Controlled Flight into Stall (CFIS): Functional complexity failures and automation surprises | |
| CN104750947A (en) | Design method of UAV (unmanned aerial vehicle) airline database and verification method of airline database | |
| CN108661808A (en) | The method of engine for twin-engined plane being automatically closed | |
| EP1837506B1 (en) | Method for monitoring thrust in gas turbine engines | |
| RU2666886C1 (en) | Method of management of the anti-icing system of the air intake of the gas turbine engine of the aircraft | |
| Cronin et al. | Integrated digital/electric aircraft concepts study | |
| US12265000B2 (en) | Diagnostic system and method for monitoring hydraulic pump | |
| Loxton et al. | First Flight of the eCaravan–magnifix and AeroTEC’s All-Electric Cessna 208B Technology Demonstrator | |
| Reynolds et al. | Power System Human Machine Interfaces for the X-57 Mod II Aircraft | |
| Zhang et al. | Distributed architecture optimal design for aircraft thrust management system with safety method | |
| Cai | Research on flight test method and risk control of civil aircraft with maximum practicable rate for rotation |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20150415 |
|
| WD01 | Invention patent application deemed withdrawn after publication |