CN109556709A - A kind of aero-engine ionic flame detector of composite structure - Google Patents
A kind of aero-engine ionic flame detector of composite structure Download PDFInfo
- Publication number
- CN109556709A CN109556709A CN201811461528.3A CN201811461528A CN109556709A CN 109556709 A CN109556709 A CN 109556709A CN 201811461528 A CN201811461528 A CN 201811461528A CN 109556709 A CN109556709 A CN 109556709A
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- engine
- detector
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- detecting electrode
- electrode
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- 239000002131 composite material Substances 0.000 title claims abstract description 11
- 239000012212 insulator Substances 0.000 claims abstract description 10
- 238000002485 combustion reaction Methods 0.000 claims abstract description 8
- 239000004642 Polyimide Substances 0.000 claims abstract description 4
- 239000000463 material Substances 0.000 claims abstract description 4
- 229920001721 polyimide Polymers 0.000 claims abstract description 4
- 238000010276 construction Methods 0.000 claims abstract description 3
- 239000000203 mixture Substances 0.000 claims description 2
- 238000001514 detection method Methods 0.000 claims 1
- 230000005611 electricity Effects 0.000 claims 1
- 230000008901 benefit Effects 0.000 description 3
- 238000010586 diagram Methods 0.000 description 3
- 230000003014 reinforcing effect Effects 0.000 description 3
- 230000004075 alteration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01J—MEASUREMENT OF INTENSITY, VELOCITY, SPECTRAL CONTENT, POLARISATION, PHASE OR PULSE CHARACTERISTICS OF INFRARED, VISIBLE OR ULTRAVIOLET LIGHT; COLORIMETRY; RADIATION PYROMETRY
- G01J1/00—Photometry, e.g. photographic exposure meter
- G01J1/42—Photometry, e.g. photographic exposure meter using electric radiation detectors
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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Spectroscopy & Molecular Physics (AREA)
- Other Investigation Or Analysis Of Materials By Electrical Means (AREA)
- Ignition Installations For Internal Combustion Engines (AREA)
Abstract
The present invention proposes a kind of aero-engine ionic flame detector of composite structure, is made of the first detector and the second detector；First detector includes the first detecting electrode, central electrode, insulator, shell and power outlet；First detecting electrode is connect with central electrode, is connect with the contact pin of power outlet, and the first measure loop is constituted；It is electrically insulated between central electrode and shell using the insulator that polyimide material is constituted；Shell is not connect with the contact pin of power outlet, is only used as support construction and is connect with engine wall；Second detector is welded to form by the second detecting electrode and ring flange；Ring flange is connect by bolt with engine wall, and the second measure loop is constituted；First detecting electrode and the second detecting electrode are extend into jointly in the combustion flame of engine chamber, are not in the situation of flame instability, and control the two threshold value, are improved ionization current signal and are detected stability.
Description
Technical field
The invention belongs to aero-engines to ionize flame detecting field, specially a kind of aero-engine of fabricated structure
Ionic flame detector.
Background technique
Ionic flame detector is for detecting whether engine augmentor is lighted, existing aero-engine ionization fire
Flame detector using integral type ionic flame detector, as shown in Figure 1, detecting electrode (1) is connect with central electrode (2)
As an electrode 1, detecting electrode is extend into engine chamber, and shell (4) is mounted in engine wall, with engine wall
It is connected, as electrode 2, is insulated between the two by insulator (3), electrode 1 is connect with the contact pin 1 of power outlet (5),
Electrode 2 is connect with the contact pin 2 of power outlet, and the alternating voltage of determining amplitude is applied between contact pin 1 and contact pin 2, when starting
When machine combustor ignition, conductive path is formed between electrode 1 and electrode 2, controller collects the electric current, issues reinforcing and lights
Signal, the structure are widely used in aero-engine.Since the flame that the structure detects is detecting electrode (1) and shell (4)
Between flame, in flame instability, easily make between detecting electrode (1) and shell (4) flame drift, lead to ionization current
It is unstable, it be easy to cause reinforcing lamp flashing wrong report.
Summary of the invention
In order to solve the problems existing in the prior art, the present invention proposes that a kind of aero-engine ionic flame of composite structure is visited
Device is surveyed, is avoided since shell is as second electrode, the problem for causing ionization current signal unstable when flare up fire is unstable,
Reinforcing lamp flashing wrong report is avoided the occurrence of, ionization current signal is improved and detects stability.
The technical solution of the present invention is as follows:
A kind of aero-engine ionic flame detector of the composite structure, it is characterised in that: by the first detector and
Second detector composition；
First detector includes the first detecting electrode, central electrode, insulator, shell and power outlet；First inspection
It surveys electrode to connect with central electrode, be connect with the contact pin of power outlet, constitute the first measure loop；Between central electrode and shell
It is electrically insulated using the insulator that polyimide material is constituted；Shell is not connect with the contact pin of power outlet, is only used as supporting
Structure is connect with engine wall；
Second detector is welded to form by the second detecting electrode and ring flange；Ring flange passes through bolt and engine wall
Connection constitutes the second measure loop；
First detecting electrode and the second detecting electrode are extend into jointly in the combustion flame of engine chamber.
Further preferred embodiment, a kind of aero-engine ionic flame detector of composite structure, feature exist
In: the threshold value of first detecting electrode and the second detecting electrode is 6cm.
Beneficial effect
Combined ion flame detector structure proposed by the present invention extend into engine using two-way detecting electrode jointly
It is not in the situation of flame instability since the two end is extend into combustion flame in the combustion flame of combustion chamber, and
And both control threshold value, it improves ionization current signal and detects stability.
Additional aspect and advantage of the invention will be set forth in part in the description, and will partially become from the following description
Obviously, or practice through the invention is recognized.
Detailed description of the invention
Above-mentioned and/or additional aspect of the invention and advantage will become from the description of the embodiment in conjunction with the following figures
Obviously and it is readily appreciated that, in which:
Fig. 1: prior art illustration；
Fig. 2: the first detector diagram；
Fig. 3: the second detector diagram；
Fig. 4: the aero-engine ionic flame detector diagram of composite structure proposed by the present invention；
Wherein: (1) detecting electrode (2) central electrode (3) insulator (4) shell (5) power outlet (6) ring flange.
Specific embodiment
The embodiment of the present invention is described below in detail, the embodiment is exemplary, it is intended to it is used to explain the present invention, and
It is not considered as limiting the invention.
As shown in figure 4, the aero-engine ionic flame detector of the composite structure in the present embodiment, by the first detector
It is formed with the second detector.
As shown in Fig. 2, first detector includes that the first detecting electrode, central electrode, insulator, shell and power supply are inserted
Seat；First detecting electrode is connect with central electrode, then is connect with the contact pin of power outlet, and the first measure loop is constituted；Middle electrocardio
It is electrically insulated between pole and shell using the insulator that polyimide material is constituted；Shell does not connect with the contact pin of power outlet
It connects, is only used as support construction and is connect with engine wall.
As shown in figure 3, second detector is welded to form by the second detecting electrode and ring flange；Ring flange passes through bolt
It is connect with engine wall, constitutes the second measure loop.
First detector and the second detector are installed in engine wall jointly, the first detecting electrode and the second detecting electrode
It is extend into the combustion flame of engine chamber jointly.It is not in fire since the two end is extend into combustion flame
The unstable situation of flame, the threshold value for controlling the first detecting electrode and the second detecting electrode is 6cm, improves ionization current signal
Detect stability.
The aero-engine ionic flame detector internal applications Mr. Yu's h type engine h for the composite structure that the present embodiment proposes
On, ground run has been passed through with engine, the results showed that, full ionization current values are stablized in 700 μ A under Afterburning condition
Near, do not occur to report phenomenon by mistake, sufficiently demonstrating structure design can greatly improve the steady of ionization current flame detector
It is qualitative.The design applies also on the engine ionic flame detector of other models, ionizes fire in military aero-engine
Flame detector field can obtain good economic benefit by wide application prospect, future.
Although the embodiments of the present invention has been shown and described above, it is to be understood that above-described embodiment is example
Property, it is not considered as limiting the invention, those skilled in the art are not departing from the principle of the present invention and objective
In the case where can make changes, modifications, alterations, and variations to the above described embodiments within the scope of the invention.
Claims (2)
1. a kind of aero-engine ionic flame detector of composite structure, it is characterised in that: visited by the first detector and second
Survey device composition；
First detector includes the first detecting electrode, central electrode, insulator, shell and power outlet；First detection electricity
Pole is connect with central electrode, is connect with the contact pin of power outlet, and the first measure loop is constituted；It is used between central electrode and shell
The insulator that polyimide material is constituted is electrically insulated；Shell is not connect with the contact pin of power outlet, is only used as support construction
It is connect with engine wall；
Second detector is welded to form by the second detecting electrode and ring flange；Ring flange is connected by bolt and engine wall
It connects, constitutes the second measure loop；
First detecting electrode and the second detecting electrode are extend into jointly in the combustion flame of engine chamber.
2. the aero-engine ionic flame detector of a kind of composite structure according to claim 1, it is characterised in that: described
The threshold value of first detecting electrode and the second detecting electrode is 6cm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811461528.3A CN109556709A (en) | 2018-12-02 | 2018-12-02 | A kind of aero-engine ionic flame detector of composite structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811461528.3A CN109556709A (en) | 2018-12-02 | 2018-12-02 | A kind of aero-engine ionic flame detector of composite structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109556709A true CN109556709A (en) | 2019-04-02 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811461528.3A Pending CN109556709A (en) | 2018-12-02 | 2018-12-02 | A kind of aero-engine ionic flame detector of composite structure |
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| Country | Link |
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| CN (1) | CN109556709A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113654805A (en) * | 2021-09-09 | 2021-11-16 | 中国航发沈阳黎明航空发动机有限责任公司 | Ion flame detector spatial position adjusting device and adjusting method |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH03102118A (en) * | 1989-09-14 | 1991-04-26 | Hitachi Ltd | Gas turbine combustor |
| US20020036192A1 (en) * | 1996-04-10 | 2002-03-28 | Yasuyuki Sato | Glow plug and method of manufacturing the same, and ion current detector |
| JP2012188936A (en) * | 2011-03-08 | 2012-10-04 | Toyota Motor Corp | Engine ignition control device |
| CN206563315U (en) * | 2017-01-17 | 2017-10-17 | 上海徐源环保科技发展有限公司 | The energy-saving kitchen range of fired state is automatically controlled by detecting flame formation |
| CN107490178A (en) * | 2017-10-09 | 2017-12-19 | 珠海格力电器股份有限公司 | Gas-heating water heater and its control method |
| CN107646085A (en) * | 2015-05-25 | 2018-01-30 | 诺沃皮尼奥内技术股份有限公司 | There are the turbofuel nozzle and gas-turbine unit of integrated form flame ion sensor |
| CN207610860U (en) * | 2017-11-08 | 2018-07-13 | 陕西航空电气有限责任公司 | A kind of aero-engine ionization flame detector |
-
2018
- 2018-12-02 CN CN201811461528.3A patent/CN109556709A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH03102118A (en) * | 1989-09-14 | 1991-04-26 | Hitachi Ltd | Gas turbine combustor |
| US20020036192A1 (en) * | 1996-04-10 | 2002-03-28 | Yasuyuki Sato | Glow plug and method of manufacturing the same, and ion current detector |
| JP2012188936A (en) * | 2011-03-08 | 2012-10-04 | Toyota Motor Corp | Engine ignition control device |
| CN107646085A (en) * | 2015-05-25 | 2018-01-30 | 诺沃皮尼奥内技术股份有限公司 | There are the turbofuel nozzle and gas-turbine unit of integrated form flame ion sensor |
| CN206563315U (en) * | 2017-01-17 | 2017-10-17 | 上海徐源环保科技发展有限公司 | The energy-saving kitchen range of fired state is automatically controlled by detecting flame formation |
| CN107490178A (en) * | 2017-10-09 | 2017-12-19 | 珠海格力电器股份有限公司 | Gas-heating water heater and its control method |
| CN207610860U (en) * | 2017-11-08 | 2018-07-13 | 陕西航空电气有限责任公司 | A kind of aero-engine ionization flame detector |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113654805A (en) * | 2021-09-09 | 2021-11-16 | 中国航发沈阳黎明航空发动机有限责任公司 | Ion flame detector spatial position adjusting device and adjusting method |
| CN113654805B (en) * | 2021-09-09 | 2024-01-30 | 中国航发沈阳黎明航空发动机有限责任公司 | Spatial position adjusting device and method for ion flame detector |
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Application publication date: 20190402 |