CN205808680U - A kind of aircraft hot gas anti-icing system fluted shape hole discharge coefficient measurement apparatus - Google Patents
A kind of aircraft hot gas anti-icing system fluted shape hole discharge coefficient measurement apparatus Download PDFInfo
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- CN205808680U CN205808680U CN201620453070.7U CN201620453070U CN205808680U CN 205808680 U CN205808680 U CN 205808680U CN 201620453070 U CN201620453070 U CN 201620453070U CN 205808680 U CN205808680 U CN 205808680U
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- discharge coefficient
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- shape hole
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Abstract
This utility model relates to aircraft hot gas anti-icing system bleed flow measurement distribution technique field, particularly to a kind of aircraft hot gas anti-icing system fluted shape hole discharge coefficient measurement apparatus, at least to solve the problem that current discharge coefficient determines method applicability and poor accuracy.Measurement apparatus includes: air supply system, is connected with bourdon's tube by bleed air line；Pressure regulating valve, is arranged in bleed air line；Mass flowmenter, in the bleed air line between pressure regulating valve and bourdon's tube；Total-pressure probe and total temperature probe, be successively set in the bleed air line between mass flowmenter and bourdon's tube；Processing means, the discharge coefficient in the fluted shape hole for obtaining according to the area of section sum in fluted shape holes all on mass flow information, stagnation pressure information, stagnation temperature information and bourdon's tube.Fluted shape hole of the present utility model discharge coefficient measurement apparatus, it is possible to the fluted shape hole for different pore size, different wall carries out discharge coefficient measurement, and the suitability is higher, and measurement result is more accurately and reliably.
Description
Technical field
This utility model relates to aircraft hot gas anti-icing system bleed flow measurement distribution technique field, flies particularly to one
Machine hot gas anti-icing system fluted shape hole discharge coefficient measurement apparatus.
Background technology
Bourdon's tube is anti-icing bleed distributing equipment commonly used in aircraft hot gas anti-icing system, is carrying out assignment of traffic meter
During calculation, on bourdon's tube, the discharge coefficient in fluted shape hole is very important parameter.At present, relevant hot gas anti-icing system flute does not also occur
The fluted shape hole discharge coefficient of shape pipe is relatively effectively and the strong assay method of the suitability or the introduction of determinator, commonly used
Method be that the discharge coefficient of reference standard orifice plate is modified further according to the Reynolds number in fluted shape hole.
But, the method has significant limitation in use, and the fluted shape hole for some aperture cannot be found and can join
The orifice examined, poor for applicability；It addition, in some cases, even if aperture matches with standard orifice plate, but wall thickness and not
With, do not account for the thick impact on discharge coefficient of fluted shape hole wall, it is impossible to accurately obtain the discharge coefficient in fluted shape hole, thus to heat
Just cannot accurately distribute anti-icing bleed flow during gas anti-icing system anti-icing bleed assignment of traffic, affect hot gas anti-icing system further
Anti-icing performance.
Summary of the invention
The purpose of this utility model there is provided a kind of aircraft hot gas anti-icing system fluted shape hole discharge coefficient measurement apparatus, with
At least solve the problem that current discharge coefficient determines method applicability and poor accuracy.
The technical solution of the utility model is:
A kind of aircraft hot gas anti-icing system fluted shape hole discharge coefficient measurement apparatus, including:
Air supply system, is connected with bourdon's tube by bleed air line；
Pressure regulating valve, is arranged in described bleed air line；
Mass flowmenter, arranges in described bleed air line, and it, between described pressure regulating valve and described bourdon's tube, is used for
Measure the mass flow of gas；
Total-pressure probe and total temperature probe, be successively set between described mass flowmenter and described bourdon's tube is described
In bleed air line, it is respectively used to measure stagnation pressure and the stagnation temperature of gas；
Processing means, for according to described mass flow information, described stagnation pressure information, described stagnation temperature information and described flute
The discharge coefficient in the described fluted shape hole that the area of section sum in all fluted shape holes obtains on shape pipe.
Optionally, described aircraft hot gas anti-icing system fluted shape hole discharge coefficient measurement apparatus also includes:
Ring flange, is connected by described ring flange between described bleed air line with described bourdon's tube.
The utility model has the advantage of:
Aircraft hot gas anti-icing system fluted shape hole of the present utility model discharge coefficient measurement apparatus, it is possible to for different pore size,
The fluted shape hole of different wall carries out discharge coefficient measurement, and the suitability is higher, and measurement result is more accurately and reliably.
Accompanying drawing explanation
Fig. 1 is the structural representation of this utility model aircraft hot gas anti-icing system fluted shape hole discharge coefficient measurement apparatus.
Detailed description of the invention
Clearer, below in conjunction with this utility model for the purpose making this utility model implement, technical scheme and advantage
Accompanying drawing in embodiment, is further described in more detail the technical scheme in this utility model embodiment.In the accompanying drawings, ad initio
Represent same or similar element to same or similar label eventually or there is the element of same or like function.Described reality
Executing example is a part of embodiment of this utility model rather than whole embodiments.The embodiment described below with reference to accompanying drawing
It is exemplary, it is intended to be used for explaining this utility model, and it is not intended that to restriction of the present utility model.Based on this practicality
Embodiment in novel, the every other reality that those of ordinary skill in the art are obtained under not making creative work premise
Execute example, broadly fall into the scope of this utility model protection.Below in conjunction with the accompanying drawings embodiment of the present utility model is described in detail.
In description of the present utility model, it is to be understood that term " " center ", " longitudinally ", " laterally ", "front", "rear",
The orientation of the instruction such as "left", "right", " vertically ", " level ", " top ", " end ", " interior ", " outward " or position relationship are for based on accompanying drawing institute
The orientation shown or position relationship, be for only for ease of description this utility model and simplify description rather than instruction or hint indication
Device or element must have specific orientation, with specific azimuth configuration and operation, therefore it is not intended that to this practicality
The restriction of novel protected scope.
1 pair of this utility model aircraft hot gas anti-icing system fluted shape hole discharge coefficient measurement apparatus is done into one below in conjunction with the accompanying drawings
Step describes in detail.
This utility model provides a kind of aircraft hot gas anti-icing system fluted shape hole discharge coefficient measurement apparatus, can include supplying
Gas system 1, pressure regulating valve 2, mass flowmenter 4, total-pressure probe 5, total temperature probe 6 and processing means 9.
Air supply system 1 is connected with bourdon's tube 8 by bleed air line 3, for providing bleed to whole measurement apparatus, it is ensured that
Pressure；Meanwhile, air supply system 1 can arrange corresponding heater, to ensure temperature.
The bleed air line 3 in air supply system 1 exit is provided with pressure regulating valve 2, for needing regulation to supply according to test
The supply gas pressure of gas system 1.
Mass flowmenter 4 arranges in bleed air line 3, and it is used for measuring supply between pressure regulating valve 2 and bourdon's tube 8
The mass flow of system 1 effluent air.
Total-pressure probe 5 and total temperature probe 6 are successively set on the bleed air line 3 between mass flowmenter 4 and bourdon's tube 8
On, it is respectively used to measure stagnation pressure and the stagnation temperature of gas.
Processing means 9 can be known multiple applicable processing means, such as PLC, microcomputer etc.；Process dress
Put 9 to be connected with mass flowmenter 4, total-pressure probe 5 and total temperature probe 6 respectively, be disposed for believing according to mass flow
The cross section (sectional plane and the central axis upright in hole) in all fluted shape holes on breath, stagnation pressure information, stagnation temperature information and bourdon's tube
The discharge coefficient in the fluted shape hole that area sum obtains；Wherein, the area of section sum in all fluted shape holes can be to lead at the trial
Cross and be input in processing means 9 after operator artificially measures.
Aircraft hot gas anti-icing system fluted shape hole of the present utility model discharge coefficient measurement apparatus, it is possible to for different pore size,
The fluted shape hole of different wall carries out discharge coefficient measurement, and the suitability is higher, and measurement result is more accurately and reliably.
Further, in the discharge coefficient measurement apparatus of fluted shape hole of the present utility model, between bleed air line 3 and bourdon's tube 8
Can be connected by ring flange 7, in order to dismantle, change bourdon's tube, there is good versatility.
Further, in the discharge coefficient measurement apparatus of fluted shape hole of the present utility model, processing means 9 is according to following relation
Formula obtains the flow coefficient C in fluted shape holeq:
Wherein, m mass flow, P is stagnation pressure, and T is stagnation temperature, and S is the area of section sum in all fluted shape holes on bourdon's tube.
The above, detailed description of the invention the most of the present utility model, but protection domain of the present utility model does not limit to
In this, any those familiar with the art in the technical scope that this utility model discloses, the change that can readily occur in
Change or replace, all should contain within protection domain of the present utility model.Therefore, protection domain of the present utility model should be with described
Scope of the claims is as the criterion.
Claims (2)
1. an aircraft hot gas anti-icing system fluted shape hole discharge coefficient measurement apparatus, it is characterised in that including:
Air supply system (1), is connected with bourdon's tube (8) by bleed air line (3)；
Pressure regulating valve (2), is arranged in described bleed air line (3)；
Mass flowmenter (4), arranges in described bleed air line (3), and it is positioned at described pressure regulating valve (2) and described bourdon's tube (8)
Between, for measuring the mass flow of gas；
Total-pressure probe (5) and total temperature probe (6), be successively set on described mass flowmenter (4) and described bourdon's tube (8) it
Between described bleed air line (3) on, be respectively used to measure the stagnation pressure of gas and stagnation temperature；
Processing means (9), for according to described mass flow information, described stagnation pressure information, described stagnation temperature information and described flute
The discharge coefficient in the described fluted shape hole that the area of section sum in all fluted shape holes obtains on shape pipe.
Aircraft hot gas anti-icing system fluted shape hole the most according to claim 1 discharge coefficient measurement apparatus, it is characterised in that also
Including:
Ring flange (7), is connected by described ring flange (7) between described bleed air line (3) with described bourdon's tube (8).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620453070.7U CN205808680U (en) | 2016-05-18 | 2016-05-18 | A kind of aircraft hot gas anti-icing system fluted shape hole discharge coefficient measurement apparatus |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620453070.7U CN205808680U (en) | 2016-05-18 | 2016-05-18 | A kind of aircraft hot gas anti-icing system fluted shape hole discharge coefficient measurement apparatus |
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| Publication Number | Publication Date |
|---|---|
| CN205808680U true CN205808680U (en) | 2016-12-14 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620453070.7U Active CN205808680U (en) | 2016-05-18 | 2016-05-18 | A kind of aircraft hot gas anti-icing system fluted shape hole discharge coefficient measurement apparatus |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112556728A (en) * | 2019-09-25 | 2021-03-26 | 中国航发商用航空发动机有限责任公司 | Anti-icing sensor and have its engine |
-
2016
- 2016-05-18 CN CN201620453070.7U patent/CN205808680U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112556728A (en) * | 2019-09-25 | 2021-03-26 | 中国航发商用航空发动机有限责任公司 | Anti-icing sensor and have its engine |
| CN112556728B (en) * | 2019-09-25 | 2022-07-19 | 中国航发商用航空发动机有限责任公司 | Anti-icing sensor and have its engine |
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