CN103900437A - Inner conical surface bouncing detection device of aircraft engine fuel nozzle - Google Patents
Inner conical surface bouncing detection device of aircraft engine fuel nozzle Download PDFInfo
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- CN103900437A CN103900437A CN201410140812.6A CN201410140812A CN103900437A CN 103900437 A CN103900437 A CN 103900437A CN 201410140812 A CN201410140812 A CN 201410140812A CN 103900437 A CN103900437 A CN 103900437A
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Abstract
The invention belongs to the detection technology, and relates to an inner conical surface bouncing detection device of an aircraft engine fuel nozzle. The inner conical surface bouncing detection device of the aircraft engine fuel nozzle is characterized by being composed of a base, a dial gage assembly, a rocker arm assembly and a locating assembly. By means of the inner conical surface bouncing detection device of the aircraft engine fuel nozzle, the operation process is simplified, the operation difficulty is reduced, the detection efficiency is improved, the detection cost is reduced, 100% detection on the fuel nozzle is achieved, and the operation safety of an aircraft engine is guaranteed.
Description
Technical field
The invention belongs to detection technique, relate to a kind of aeromotor fuel nozzle inner conical surface jitter detection apparatus.
Background technology
The structure of certain type aeromotor fuel nozzle is referring to Fig. 1, its inner chamber is from left to right divided into spray orifice section, inner conical surface section and straight hole section 3 parts, cone angle=50 of inner conical surface section °～90 °, the internal diameter of straight hole section is d, having external diameter at the right-hand member of straight hole section is the flange of D, the jerk value on the face of cylinder of the relative flange of inner conical surface P of inner conical surface section is not more than 0.03mm, is L from the right side of flange to the distance of inner conical surface section left end, is L1 from the right side of flange to the distance of inner conical surface section right-hand member.Its effect is that the fuel oil of the cyclone of flowing through is carried out to throttling supercharging, to reach certain flow, angle, atomization requirement.The quality of beating of the reducing-pitch thread inner chamber conical surface and cylindrical or endoporus directly affects the spray angle of fuel oil, if jerk value is larger, after packing into, cyclone can produce deflection, impel ejection fuel oil towards one side deflection, may cause on the direct directive fuel manifold of fuel oil or casing, affect the safety and reliability of engine.At present, fuel nozzle reducing-pitch thread inner chamber conical surface glitch detection mainly relies on cylindricity instrument to inspect by random samples, and because the reducing-pitch thread inner chamber of nozzle is generally Small-deep Hole, the inner diameter d of straight hole section is only 3mm～6mm.While using roundness measuring equipment equipment Inspection, operating personnel are required very highly, whole detection need to be finely tuned repeatedly, detection difficulty is large, inefficiency and limitation large.Simultaneously, adopt the method for this sampling observation cannot accomplish the monitoring to all product qualities, in process, because parts fixation error, tool wear, lathe be unstable etc., the reducing-pitch thread inner chamber conical surface that factor causes beats that deviation cannot be found, causes unstable product quality.
Summary of the invention
The object of the invention is: a kind of aeromotor fuel nozzle inner conical surface jitter detection apparatus is provided, to simplify the operation course, reduces operation easier, improve detection efficiency, reduce testing cost, realize 100% detection that fuel nozzle inner conical surface is beated, ensure the security of operation of aeromotor.
Technical scheme of the present invention is: aeromotor fuel nozzle inner conical surface jitter detection apparatus, the inner chamber of detected fuel nozzle is from left to right divided into spray orifice section, inner conical surface section and straight hole section 3 parts, cone angle=50 of inner conical surface section °～90 °, the internal diameter of straight hole section is d, having external diameter at the right-hand member of straight hole section is the flange of D, the jerk value on the face of cylinder of the relative flange of inner conical surface P of inner conical surface section is not more than 0.03mm, being L from the right side of flange to the distance of inner conical surface section left end, is L1 from the right side of flange to the distance of inner conical surface section right-hand member, it is characterized in that: said inner conical surface jitter detection apparatus is made up of base, dial gauge assembly, rocker arm assembly and positioning component, base 1 is a rectangular slab, dial gauge assembly is made up of dial gauge bearing 2, lining 11, housing screw 12 and dial gauge 13, dial gauge bearing 2 is plates with bending that an xsect is rectangle, it forms by the lower vertical section perpendicular to base with the top construction section at inclination angle, angle β=40 of vertical section and construction section °～60 °, the lower surface of dial gauge bearing 2 vertical sections is fixed by screws in the right of base 1 upper surface, on the plate face of construction section, there is a dial gauge mounting hole, on the upper surface of construction section, there is a threaded hole connecting with dial gauge mounting hole, housing screw 12 is screwed in above-mentioned threaded hole, the connecting rod of dial gauge 13 is arranged in dial gauge mounting hole and keeps clearance fit, by housing screw 12, dial gauge 13 is locked, rocker arm assembly is made up of rocking arm 3, rocker arm support 4 and bearing pin 8, rocking arm 3 is by gage beam 3a, 3b connects to form with transmission arm, connecting portion at gage beam 3a and transmission arm 3b has a rocking arm pin-and-hole 3c, there is a hemispheric measuring head 3d in the end of gage beam 3a, the hemisphere face of measuring head 3d is downward, on the right surface of transmitting arm 3b, there is one to transmit plane 3g near the position of termination, between transmission plane 3g and rocking arm pin-and-hole 3c, there is spring hanging hole 3f, the line of the centre of sphere point 3e of measuring head 3d and rocking arm pin-and-hole 3c central point is perpendicular to the plane of transmitting plane 3g place, be M from the centre of sphere point 3e of measuring head 3d to the distance of rocking arm pin-and-hole 3c central point, the lower surface of rocker arm support 4 is fixed by screws on base 1, be positioned at the left side of dial gauge bearing 2, top of rocker arm support 4 is the ears with pin-and-hole, bearing pin 8 is through the pin-and-hole of rocker arm support 4 top ears and the rocking arm pin-and-hole 3c of rocking arm 3, rocking arm 3 and rocker arm support 4 are formed to chain connection, the transmission plane 3g that transmits arm 3b vertically contacts with the gauge head of dial gauge 13, and the distance between the axis of rocking arm pin-and-hole 3c and dial gauge 13 gauge head axis is M, positioning component is made up of 2 band convex shoulder register pins 5, positioning support 6, blind rivet 9 and springs 10, positioning support 6 is plates with bending that an xsect is rectangle, it forms by the lower vertical section perpendicular to base with the top positioning section at inclination angle, the angle of vertical section and positioning section is β, the lower surface of positioning support 6 vertical sections is fixed by screws on base 1, be positioned at the left side of rocker arm support 4, on the plate face of positioning section, there is a measured hole, below measured hole, each side there is a pin-and-hole, 2 band convex shoulder register pins 5 are arranged on respectively in above-mentioned pin-and-hole and keep interference fit, when detected fuel nozzle 7 is placed on the plate face of positioning section, when the circumference of flange and 2 convex shoulders with convex shoulder register pin 5 are fitted, the interior axially bored line of detected fuel nozzle 7 and the axis coaxle of measured hole, blind rivet 9 is optical axises, there is a radially through hole on the top of blind rivet 9, there is a blind rivet installing blind at the upper surface center of positioning section, the bottom of blind rivet 9 is positioned at blind rivet installing blind and keeps interference fit, the axis of blind rivet 9 and the axis of measured hole are orthogonal, the upper end of spring 10 hangs on the radially through hole on blind rivet 9 tops, and the lower end of spring 10 hangs on the spring hanging hole 3f transmitting on arm 3b, the gage beam 3a of rocking arm 3 stretches in the endoporus of detected fuel nozzle 7 after passing the measured hole on positioning support 6, and the measuring head 3d of gage beam 3a contacts with the inner conical surface P of inner conical surface section, is N from rocking arm pin-and-hole 3c central point to the distance of the left surface of positioning section, meet the following conditions apart from M: L1+N < M < L+N.
Advantage of the present invention is: a kind of aeromotor fuel nozzle inner conical surface jitter detection apparatus is provided, has simplified operating process, reduced operation easier, improve detection efficiency, reduce testing cost, realized 100% of fuel nozzle and detected, ensured the security of operation of aeromotor.
Brief description of the drawings
Fig. 1 is the structural representation of certain type aeromotor fuel nozzle.
Fig. 2 is structural representation of the present invention.
Fig. 3 is that the K of Fig. 2 is to partial view.In figure, the upper left side of drawing is the left of positioning support 6, and the lower right of drawing is the right-hand of positioning support 6, and the upper right side of drawing is the top of positioning support 6.
Fig. 4 is the structural representation of rocking arm 3 in the present invention.
Embodiment
Below the present invention is described in further details.Referring to Fig. 1 to Fig. 4, aeromotor fuel nozzle inner conical surface jitter detection apparatus, the inner chamber of detected fuel nozzle is from left to right divided into spray orifice section, inner conical surface section and straight hole section 3 parts, cone angle=50 of inner conical surface section °～90 °, the internal diameter of straight hole section is d, having external diameter at the right-hand member of straight hole section is the flange of D, the jerk value on the face of cylinder of the relative flange of inner conical surface P of inner conical surface section is not more than 0.03mm, being L from the right side of flange to the distance of inner conical surface section left end, is L1 from the right side of flange to the distance of inner conical surface section right-hand member, it is characterized in that: said inner conical surface jitter detection apparatus is made up of base, dial gauge assembly, rocker arm assembly and positioning component, base 1 is a rectangular slab, dial gauge assembly is made up of dial gauge bearing 2, lining 11, housing screw 12 and dial gauge 13, dial gauge bearing 2 is plates with bending that an xsect is rectangle, it forms by the lower vertical section perpendicular to base with the top construction section at inclination angle, angle β=40 of vertical section and construction section °～60 °, the lower surface of dial gauge bearing 2 vertical sections is fixed by screws in the right of base 1 upper surface, on the plate face of construction section, there is a dial gauge mounting hole, on the upper surface of construction section, there is a threaded hole connecting with dial gauge mounting hole, housing screw 12 is screwed in above-mentioned threaded hole, the connecting rod of dial gauge 13 is arranged in dial gauge mounting hole and keeps clearance fit, by housing screw 12, dial gauge 13 is locked, rocker arm assembly is made up of rocking arm 3, rocker arm support 4 and bearing pin 8, rocking arm 3 is by gage beam 3a, 3b connects to form with transmission arm, connecting portion at gage beam 3a and transmission arm 3b has a rocking arm pin-and-hole 3c, there is a hemispheric measuring head 3d in the end of gage beam 3a, the hemisphere face of measuring head 3d is downward, on the right surface of transmitting arm 3b, there is one to transmit plane 3g near the position of termination, between transmission plane 3g and rocking arm pin-and-hole 3c, there is spring hanging hole 3f, the line of the centre of sphere point 3e of measuring head 3d and rocking arm pin-and-hole 3c central point is perpendicular to the plane of transmitting plane 3g place, be M from the centre of sphere point 3e of measuring head 3d to the distance of rocking arm pin-and-hole 3c central point, the lower surface of rocker arm support 4 is fixed by screws on base 1, be positioned at the left side of dial gauge bearing 2, top of rocker arm support 4 is the ears with pin-and-hole, bearing pin 8 is through the pin-and-hole of rocker arm support 4 top ears and the rocking arm pin-and-hole 3c of rocking arm 3, rocking arm 3 and rocker arm support 4 are formed to chain connection, the transmission plane 3g that transmits arm 3b vertically contacts with the gauge head of dial gauge 13, and the distance between the axis of rocking arm pin-and-hole 3c and dial gauge 13 gauge head axis is M, positioning component is made up of 2 band convex shoulder register pins 5, positioning support 6, blind rivet 9 and springs 10, positioning support 6 is plates with bending that an xsect is rectangle, it forms by the lower vertical section perpendicular to base with the top positioning section at inclination angle, the angle of vertical section and positioning section is β, the lower surface of positioning support 6 vertical sections is fixed by screws on base 1, be positioned at the left side of rocker arm support 4, on the plate face of positioning section, there is a measured hole, below measured hole, each side there is a pin-and-hole, 2 band convex shoulder register pins 5 are arranged on respectively in above-mentioned pin-and-hole and keep interference fit, when detected fuel nozzle 7 is placed on the plate face of positioning section, when the circumference of flange and 2 convex shoulders with convex shoulder register pin 5 are fitted, the interior axially bored line of detected fuel nozzle 7 and the axis coaxle of measured hole, blind rivet 9 is optical axises, there is a radially through hole on the top of blind rivet 9, there is a blind rivet installing blind at the upper surface center of positioning section, the bottom of blind rivet 9 is positioned at blind rivet installing blind and keeps interference fit, the axis of blind rivet 9 and the axis of measured hole are orthogonal, the upper end of spring 10 hangs on the radially through hole on blind rivet 9 tops, and the lower end of spring 10 hangs on the spring hanging hole 3f transmitting on arm 3b, the gage beam 3a of rocking arm 3 stretches in the endoporus of detected fuel nozzle 7 after passing the measured hole on positioning support 6, and the measuring head 3d of gage beam 3a contacts with the inner conical surface P of inner conical surface section, is N from rocking arm pin-and-hole 3c central point to the distance of the left surface of positioning section, meet the following conditions apart from M: L1+N < M < L+N.
The method that uses the present invention to measure is: after the gage beam 3a by the endoporus of detected fuel nozzle 7 by rocking arm 3, be placed on the positioning section plate face of positioning support 6, the circumference of flange and 2 convex shoulders with convex shoulder register pin 5 fit → are arranged on the connecting rod of dial gauge 13 in the dial gauge mounting hole of dial gauge bearing 2, the gauge head that makes dial gauge 13 contacts with the transmission plane 3g that transmits arm 3b and keeps impaction state, regulate the circumferential position of dial gauge 13 dial plates to make indicator point to zero-bit → manually rotate detected fuel nozzle 7 one weeks or several weeks along the flange axis of detected fuel nozzle 7, in the process of above-mentioned rotation, need to meet the following conditions: keep detected fuel nozzle 7 to be placed on the location-plate face of positioning support 6, the face of cylinder of flange and 2 convex shoulder laminatings with convex shoulder register pin 5, rotary course can be noncontinuity → meeting the jerk value that the maximum variation of observing dial gauge indicator under above-mentioned rotary course condition is the face of cylinder of the relative flange of P face of detected fuel nozzle 7.
Claims (1)
1. aeromotor fuel nozzle inner conical surface jitter detection apparatus, the inner chamber of detected fuel nozzle is from left to right divided into spray orifice section, inner conical surface section and straight hole section 3 parts, cone angle=50 of inner conical surface section °～90 °, the internal diameter of straight hole section is d, having external diameter at the right-hand member of straight hole section is the flange of D, the jerk value on the face of cylinder of the relative flange of inner conical surface P of inner conical surface section is not more than 0.03mm, being L from the right side of flange to the distance of inner conical surface section left end, is L1 from the right side of flange to the distance of inner conical surface section right-hand member, it is characterized in that: said inner conical surface jitter detection apparatus is made up of base, dial gauge assembly, rocker arm assembly and positioning component, base (1) is a rectangular slab, dial gauge assembly is made up of dial gauge bearing (2), lining (11), housing screw (12) and dial gauge (13), dial gauge bearing (2) is the plate with bending that an xsect is rectangle, it forms by the lower vertical section perpendicular to base with the top construction section at inclination angle, angle β=40 of vertical section and construction section °～60 °, the lower surface of dial gauge bearing (2) vertical section is fixed by screws in the right of base (1) upper surface, on the plate face of construction section, there is a dial gauge mounting hole, on the upper surface of construction section, there is a threaded hole connecting with dial gauge mounting hole, housing screw (12) is screwed in above-mentioned threaded hole, the connecting rod of dial gauge (13) is arranged in dial gauge mounting hole and keeps clearance fit, by housing screw (12), dial gauge (13) is locked, rocker arm assembly is made up of rocking arm (3), rocker arm support (4) and bearing pin (8), rocking arm (3) is by gage beam (3a), connect to form with transmission arm (3b), connecting portion at gage beam (3a) and transmission arm (3b) has a rocking arm pin-and-hole (3c), there is a hemispheric measuring head (3d) in the end of gage beam (3a), the hemisphere face of measuring head (3d) is downward, on the right surface of transmitting arm (3b), there is one to transmit plane (3g) near the position of termination, between transmission plane (3g) and rocking arm pin-and-hole (3c), there is spring hanging hole (3f), the line of the centre of sphere point (3e) of measuring head (3d) and rocking arm pin-and-hole (3c) central point is perpendicular to the plane of transmitting plane (3g) place, be M from the centre of sphere point (3e) of measuring head (3d) to the distance of rocking arm pin-and-hole (3c) central point, the lower surface of rocker arm support (4) is fixed by screws on base (1), be positioned at the left side of dial gauge bearing (2), the top of rocker arm support (4) is the ears with pin-and-hole, bearing pin (8) is through the pin-and-hole of rocker arm support (4) top ears and the rocking arm pin-and-hole (3c) of rocking arm (3), rocking arm (3) and rocker arm support (4) are formed to chain connection, the transmission plane (3g) of transmitting arm (3b) vertically contacts with the gauge head of dial gauge (13), distance between the axis of rocking arm pin-and-hole (3c) and dial gauge (13) gauge head axis is M, positioning component is made up of 2 band convex shoulder register pin (5), positioning support (6), blind rivet (9) and springs (10), positioning support (6) is the plate with bending that an xsect is rectangle, it forms by the lower vertical section perpendicular to base with the top positioning section at inclination angle, the angle of vertical section and positioning section is β, the lower surface of positioning support (6) vertical section is fixed by screws on base (1), be positioned at the left side of rocker arm support (4), on the plate face of positioning section, there is a measured hole, below measured hole, each side there is a pin-and-hole, 2 band convex shoulder register pins (5) are arranged on respectively in above-mentioned pin-and-hole and keep interference fit, when detected fuel nozzle (7) is placed on the plate face of positioning section, when the convex shoulder of the circumference of flange and 2 band convex shoulder register pins (5) is fitted, the interior axially bored line of detected fuel nozzle (7) and the axis coaxle of measured hole, blind rivet (9) is an optical axis, there is a radially through hole on the top of blind rivet (9), there is a blind rivet installing blind at the upper surface center of positioning section, the bottom of blind rivet (9) is positioned at blind rivet installing blind and keeps interference fit, the axis of blind rivet (9) and the axis of measured hole are orthogonal, the upper end of spring (10) hangs on the radially through hole on blind rivet (9) top, and the lower end of spring (10) hangs on the spring hanging hole (3f) transmitting on arm (3b), the gage beam (3a) of rocking arm (3) stretches in the endoporus of detected fuel nozzle (7) after passing the measured hole on positioning support (6), the measuring head (3d) of gage beam (3a) contacts with the inner conical surface P of inner conical surface section, is N from rocking arm pin-and-hole (3c) central point to the distance of the left surface of positioning section, meet the following conditions apart from M: (L1+N) < M < (L+N).
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| CN201410140812.6A CN103900437B (en) | 2014-04-10 | 2014-04-10 | Aero-engine fuel nozzle inner conical surface jitter detection apparatus |
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| CN201410140812.6A CN103900437B (en) | 2014-04-10 | 2014-04-10 | Aero-engine fuel nozzle inner conical surface jitter detection apparatus |
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| CN103900437A true CN103900437A (en) | 2014-07-02 |
| CN103900437B CN103900437B (en) | 2016-08-17 |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105710606A (en) * | 2015-11-25 | 2016-06-29 | 沈阳黎明航空发动机(集团)有限责任公司 | Machining method of gas generator nozzle head |
| CN107421414A (en) * | 2017-06-30 | 2017-12-01 | 天津天海同步科技有限公司 | A kind of axial workpiece internal spline bounce gauge |
| CN111750758A (en) * | 2020-06-30 | 2020-10-09 | 中国航发动力股份有限公司 | Method and device for detecting diameter and length size of conical surface and machining method |
| CN111879214A (en) * | 2020-07-31 | 2020-11-03 | 四川航天长征装备制造有限公司 | High-precision inner conical surface taper rapid detection tool |
| CN111879215A (en) * | 2020-08-03 | 2020-11-03 | 四川航天长征装备制造有限公司 | High-precision inner conical surface taper rapid detection tool and detection method |
| CN112414257A (en) * | 2021-01-14 | 2021-02-26 | 桂林福达重工锻造有限公司 | Crankshaft blank center hole runout testing fixture |
| CN113865458A (en) * | 2021-10-25 | 2021-12-31 | 中国航发贵州黎阳航空动力有限公司 | Device and method for measuring runout of inner profile surface and outer circle of aero-engine part |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN105710606A (en) * | 2015-11-25 | 2016-06-29 | 沈阳黎明航空发动机(集团)有限责任公司 | Machining method of gas generator nozzle head |
| CN107421414A (en) * | 2017-06-30 | 2017-12-01 | 天津天海同步科技有限公司 | A kind of axial workpiece internal spline bounce gauge |
| CN111750758A (en) * | 2020-06-30 | 2020-10-09 | 中国航发动力股份有限公司 | Method and device for detecting diameter and length size of conical surface and machining method |
| CN111750758B (en) * | 2020-06-30 | 2022-04-26 | 中国航发动力股份有限公司 | Method and device for detecting diameter and length size of conical surface and machining method |
| CN111879214A (en) * | 2020-07-31 | 2020-11-03 | 四川航天长征装备制造有限公司 | High-precision inner conical surface taper rapid detection tool |
| CN111879215A (en) * | 2020-08-03 | 2020-11-03 | 四川航天长征装备制造有限公司 | High-precision inner conical surface taper rapid detection tool and detection method |
| CN112414257A (en) * | 2021-01-14 | 2021-02-26 | 桂林福达重工锻造有限公司 | Crankshaft blank center hole runout testing fixture |
| CN112414257B (en) * | 2021-01-14 | 2022-05-06 | 桂林福达重工锻造有限公司 | Crankshaft blank center hole runout testing fixture |
| CN113865458A (en) * | 2021-10-25 | 2021-12-31 | 中国航发贵州黎阳航空动力有限公司 | Device and method for measuring runout of inner profile surface and outer circle of aero-engine part |
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| CN103900437B (en) | 2016-08-17 |
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Address after: Fengcheng Weiyang District ten road 710021 Shaanxi city of Xi'an Province Patentee after: AECC AVIATION POWER CO,LTD. Address before: Fengcheng Weiyang District ten road 710021 Shaanxi city of Xi'an Province Patentee before: AVIC AVIATION ENGINE Corp.,PLC Address after: Fengcheng Weiyang District ten road 710021 Shaanxi city of Xi'an Province Patentee after: AVIC AVIATION ENGINE Corp.,PLC Address before: Fengcheng Weiyang District ten road 710021 Shaanxi city of Xi'an Province Patentee before: XI'AN AVIATION POWER Co.,Ltd. |
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