CN114571117A - Machining method for fuel nozzle assembly of aircraft engine - Google Patents
Machining method for fuel nozzle assembly of aircraft engine Download PDFInfo
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- CN114571117A CN114571117A CN202210390816.4A CN202210390816A CN114571117A CN 114571117 A CN114571117 A CN 114571117A CN 202210390816 A CN202210390816 A CN 202210390816A CN 114571117 A CN114571117 A CN 114571117A
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- 239000000446 fuel Substances 0.000 title claims abstract description 28
- 238000000034 method Methods 0.000 title claims description 19
- 238000003754 machining Methods 0.000 title claims description 13
- 238000005219 brazing Methods 0.000 claims abstract description 77
- 238000003466 welding Methods 0.000 claims abstract description 36
- 239000000945 filler Substances 0.000 claims abstract description 27
- 229910052751 metal Inorganic materials 0.000 claims abstract description 27
- 239000002184 metal Substances 0.000 claims abstract description 27
- 239000011888 foil Substances 0.000 claims abstract description 21
- 238000010894 electron beam technology Methods 0.000 claims abstract description 20
- 229910001069 Ti alloy Inorganic materials 0.000 claims abstract description 7
- 239000000463 material Substances 0.000 claims abstract description 6
- 238000010146 3D printing Methods 0.000 claims abstract 2
- KDLHZDBZIXYQEI-UHFFFAOYSA-N Palladium Chemical compound [Pd] KDLHZDBZIXYQEI-UHFFFAOYSA-N 0.000 claims description 4
- 238000003672 processing method Methods 0.000 claims description 4
- 238000005507 spraying Methods 0.000 claims description 4
- 238000000227 grinding Methods 0.000 claims description 3
- 238000004519 manufacturing process Methods 0.000 claims description 3
- 229910000679 solder Inorganic materials 0.000 claims description 3
- 238000005476 soldering Methods 0.000 claims description 3
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 claims description 2
- 229910052748 manganese Inorganic materials 0.000 claims description 2
- 230000013011 mating Effects 0.000 claims description 2
- 229910000510 noble metal Inorganic materials 0.000 claims description 2
- 229910052763 palladium Inorganic materials 0.000 claims description 2
- 239000002994 raw material Substances 0.000 claims description 2
- 229910052709 silver Inorganic materials 0.000 claims description 2
- 239000004332 silver Substances 0.000 claims description 2
- 229910052718 tin Inorganic materials 0.000 claims description 2
- 239000010936 titanium Substances 0.000 claims description 2
- 229910052719 titanium Inorganic materials 0.000 claims description 2
- 229910052720 vanadium Inorganic materials 0.000 claims description 2
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 claims 2
- 229910052786 argon Inorganic materials 0.000 claims 1
- 238000010438 heat treatment Methods 0.000 claims 1
- 238000012360 testing method Methods 0.000 description 22
- 239000003921 oil Substances 0.000 description 19
- 239000007921 spray Substances 0.000 description 14
- 238000002347 injection Methods 0.000 description 9
- 239000007924 injection Substances 0.000 description 9
- 239000000295 fuel oil Substances 0.000 description 8
- 238000002485 combustion reaction Methods 0.000 description 5
- 238000007689 inspection Methods 0.000 description 5
- 238000007789 sealing Methods 0.000 description 5
- 230000010485 coping Effects 0.000 description 3
- 238000004140 cleaning Methods 0.000 description 2
- 238000001514 detection method Methods 0.000 description 2
- 238000009826 distribution Methods 0.000 description 2
- 239000007788 liquid Substances 0.000 description 2
- 239000010687 lubricating oil Substances 0.000 description 2
- 238000003801 milling Methods 0.000 description 2
- 239000010705 motor oil Substances 0.000 description 2
- 230000001133 acceleration Effects 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 230000000712 assembly Effects 0.000 description 1
- 238000000429 assembly Methods 0.000 description 1
- 238000000889 atomisation Methods 0.000 description 1
- 238000005520 cutting process Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000002594 fluoroscopy Methods 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K28/00—Welding or cutting not covered by any of the preceding groups, e.g. electrolytic welding
- B23K28/02—Combined welding or cutting procedures or apparatus
Abstract
The fuel nozzle assembly of the aircraft engine comprises a main oil way, an auxiliary nozzle adapter section, a main nozzle, an auxiliary nozzle, an adapter pipe, a rear cover plate, a first-stage swirler, a second-stage swirler and a nozzle shell; the main oil circuit and the auxiliary oil circuit are parallel pipelines at the inclined lower part, the parallel pipelines are bent into a main nozzle and an auxiliary nozzle of a horizontal concentric tube structure through an adapter tube, the adapter tube is a vertical tube and is connected to an inner tube of the horizontal concentric tube, the contact surface of the end surface of an outer tube of the concentric tube at the outer side of the adapter tube is an easy-leakage part, a brazing material groove is additionally arranged at the brazing position of the main nozzle, namely the outer tube of the concentric tube at the contact part of the main nozzle and the adapter tube, and the height and the width of the cross section of the groove are both 1-1.5 mm; forming a foil by using the brazing filler metal for titanium alloy brazing, folding and placing the foil in a brazing filler metal groove, wherein the width of the formed foil of the brazing filler metal is the width of the brazing filler metal groove, and then performing vacuum brazing; and the second-stage swirler and the nozzle shell are welded by using electron beams, the nozzle shell is a 3D printing piece, the inner cavity of the swirler is matched with the turning rabbet at the outer cavity end of the nozzle shell to be concentric, and then the electron beam welding is carried out.
Description
Technical Field
The invention relates to a processing method of an aircraft engine fuel nozzle assembly.
Background
The fuel nozzle in the aircraft engine is used for spraying fuel into a combustion chamber and atomizing the fuel into tiny oil droplets to form required concentration distribution and ensure good combustion. The fuel can be stably and accurately supplied to the combustion chamber under different working states of the engine, the atomization quality and the proper spray cone angle are ensured, and the fuel forms a certain concentration distribution in the combustion chamber.
The structure of the aircraft engine fuel nozzle is a nozzle assembly with double paths, double chambers and double nozzles, and the structure is shown in the following figure 1.
The machining method of the fuel spray nozzle of the CN201710785151.6 aeroengine and the seven-shaft turning and milling combined machining machine tool clamp a first end of a bar by using a first main shaft, machine a part with a spray cylinder on a second end opposite to the first end of the bar, and correspondingly machine an end face groove, a plurality of first inclined holes and a plurality of second inclined holes on the spray cylinder; horizontally butting the second main shaft with the first main shaft, clamping the excircle of the spray cylinder by using the second main shaft, and cutting off a part with the spray cylinder by using a cutting-off tool; and (3) overturning the second main shaft, processing a nozzle on the cut part with the nozzle barrel, and correspondingly processing an end face, an outer conical surface, an inner conical surface and a plurality of third inclined holes on the nozzle to complete the processing of the aircraft engine oil nozzle. The machining method of the aircraft engine oil nozzle and the seven-axis turning and milling combined machining machine tool provided by the invention can complete all machining of parts by one-time clamping
CN201610735874.0 an engine fuel oil injection system component for aerospace and a fuel oil injection method thereof, comprising a plurality of bottle-shaped main pipes and a plurality of sections of arc-shaped pipes, wherein the bottle-shaped main pipes are mutually communicated through the arc-shaped pipes to form an annular whole; the upper end of the bottle-shaped main pipe body is provided with a fuel oil spray nozzle, an air inlet guide vane fan is arranged outside the fuel oil spray nozzle, and an outer cover body is arranged outside the air inlet guide vane fan; the lower end of each bottle-shaped main pipe body is provided with a pressure relief oil return nozzle and an oil inlet nozzle at intervals. The oil pressure of each oil injection nozzle is controlled by adopting the pressure relief oil return nozzle, so that fuel oil is uniformly delivered to each oil injection nozzle; meanwhile, the spiral guide vane fan is adopted, air forms cyclone after passing through the spiral guide vane fan, and the cyclone further tears and atomizes fuel oil, so that the fuel oil and the air are mixed more sufficiently, the fuel oil is more sufficient in a combustion chamber, and the output power is stronger.
The invention provides a processing method of a fuel nozzle assembly of an aircraft engine.
Disclosure of Invention
The invention aims to provide a processing method suitable for the sealing performance of a main oil circuit and an auxiliary oil circuit of a fuel nozzle assembly of an aircraft engine, which cannot be ensured by the existing processing flow.
The technical scheme of the invention is that the fuel nozzle component of the aircraft engine comprises the following workpieces: the main oil way, the auxiliary nozzle adapter section, the main nozzle, the auxiliary nozzle, the adapter pipe, the rear cover plate, the first-stage swirler, the second-stage swirler and the nozzle shell; the first-stage swirler and the second-stage swirler are sleeve structures with gaps and are respectively sleeved on the auxiliary nozzle of the inner pipe of the concentric pipe and the end part of the nozzle shell; the main oil circuit and the auxiliary oil circuit are parallel pipelines at the inclined lower part, the parallel pipelines are bent into a main nozzle and an auxiliary nozzle of a horizontal concentric tube structure through an adapter tube, the adapter tube is a vertical tube and is connected to an inner tube of the horizontal concentric tube, the contact surface of the end surface (connected to the main nozzle) of an outer tube of the concentric tube at the outer side of the adapter tube is a leakage-prone part, a brazing material groove is additionally arranged at the brazing position of the main nozzle, namely the outer tube of the concentric tube at the contact part of the main nozzle and the adapter tube, and the height and the width of the cross section of the groove are both 1-1.5 mm; forming a foil by using a brazing filler metal for titanium alloy brazing, folding and placing the foil in a brazing filler metal groove, wherein the width of the formed foil of the brazing filler metal is the width of the brazing filler metal groove, and then performing vacuum brazing; the second-stage swirler and the nozzle shell are welded by electron beams, the nozzle shell is a 3D printed part, the second-stage swirler and the nozzle shell are structurally optimized and machined, the inner cavities of the second-stage swirlers and the outer cavity end turning rabbets of the nozzle shell are matched and fixed concentrically, and then the two parts are welded by the electron beams.
The machining method of the fuel nozzle assembly of the aircraft engine is characterized in that the clearance of a workpiece is 0.03-0.05 mm; filling solder foil in gaps of the soldering points;
the machining method of the fuel nozzle assembly of the aircraft engine comprises the following steps that the matching surface of a main nozzle and a nozzle shell is a welding surface, a brazing filler metal groove is additionally arranged on the welding surface, and the height and the width of the cross section of the groove are both 1-1.5 mm; after being formed into a foil by the brazing filler metal for titanium alloy brazing, the foil is folded and placed in a brazing filler metal groove, the width of the formed foil of the brazing filler metal is the width of the brazing filler metal groove, and then vacuum brazing is carried out.
Has the advantages that: the structure of the fuel nozzle component of the aircraft engine is extremely complex, the requirement of the multi-layer overlapping precision of various tube pieces is extremely high, the precision basically reaches 10 micrometers or higher, the fuel injection of main and auxiliary channels is extremely high, the requirements of the drop and the angle of the fuel injection are also extremely high, the combination of the air paths is also provided, only the fuel injection oil paths of the main and auxiliary channels are provided in the drawing, an air channel is not drawn in the structural diagram, the fuel injection of the existing main and auxiliary channels leaks and is difficult to detect, and the fuel injection control of the fuel nozzle component of the aircraft engine is influenced.
Drawings
FIG. 1 is a schematic structural view of a nozzle assembly;
FIG. 2 is a more detailed view of the weld joint of FIG. 1;
FIG. 3 is a schematic view of the structure of the mating surfaces of the member 6 (main nozzle) and the member 9 (nozzle housing) at one of the points of vulnerability to leakage;
FIG. 4 is a schematic view of the sealing of the secondary oil path on the outer circle of the secondary nozzle and the secondary nozzle;
FIG. 5 is a schematic structural view of the second stage swirler being concentrically positioned with the nozzle housing prior to electron beam welding of the two pieces;
fig. 6 is a schematic view of a first time piece;
FIG. 7 is a schematic view of a second braze;
FIG. 8 is a schematic view of an electron beam weld.
Detailed Description
As shown in the figure, the auxiliary nozzle adapter section 1, the auxiliary nozzle 2, the auxiliary nozzle 3, the adapter pipe 4, the rear cover plate 5, the main nozzle 6, the second-stage swirler 7, the first-stage swirler 8 and the nozzle shell 9. A main oil path 10, an auxiliary oil path 11, easy leakage points L1 and L2; and welding positions of the brazing H and the electronic welding D. The numerical labels are also illustrated with respect to workpieces 1-11.
Fig. 1-2 are final assembly views and details of the nozzle, relating to the procedures of brazing, electron beam welding, gas seal test, lubricating oil seal test, post-weld main and auxiliary nozzle flow and spray cone angle tests, primary and secondary swirler air flow tests and the like. From the structure and production practice of fig. 2, it can be analyzed that the contact point of the primary and secondary oil passages 10 and 11 is a leakage-prone point, i.e., a leakage-prone point L1 in the figure and a leakage-prone point L2 of the secondary oil passage at the brazing of the member 4 (adapter tube).
One of the easy leakage points is the matching surface of the piece 6 (main nozzle) and the piece 9 (nozzle shell), one important index of the brazing quality is the gap requirement of the welding surface, and the gap is usually 0.03-0.05 better. And (4) according to the tolerance of the design drawing and the brazing requirement, tightening the tolerance of the machining size of the part to meet the brazing requirement. Because the fitting of the part 6 and the part 9 has a gap, so that the condition of non-uniformity exists during the assembly of the circumferential gap, an easy leakage point L1 exists at the excircle of the part 6 (main nozzle) penetrating part 4 (adapter tube), in order to solve the problem, the processing of the main nozzle of the part 6 is optimized, a brazing filler metal groove is additionally arranged at the excircle of the contact part of the main nozzle (cylindrical position) of the part and the adapter tube, the length and the width of the cross section of the groove are both 1-1.5mm, and the structure is shown in figure 3.
The left side of the easy leakage point L2 is sealed by a piece 5 (back cover plate), and the right side is not provided with a sealing area, so that the easy leakage point L2 is formed. In view of this, sealing of the secondary oil path is achieved by optimizing the machining of the pieces 2 (secondary nozzles) and 3 (i.e. on the excircle of the cylinder of the secondary nozzle).
The problem of two concentric positioning before welding exists in the electron beam welding of a piece 7 (a second-stage swirler) and a piece 9 (a nozzle shell), because the nozzle shell of the piece 9 is a 3D printed piece, an available positioning surface (an inner cavity surface) of a part of the nozzle shell is a non-processing area, centering is difficult, the structure of the second-stage swirler and the structure of the nozzle shell are optimized and processed by the technical scheme, the two concentric positioning structures are matched and fixed through the inner cavities of the two second-stage swirlers and the outer cavity end turning rabbets of the nozzle shell, welding quality is not influenced at the same time, and the structure is shown in figure 5.
The first brazing is shown in fig. 6; the processing flow comprises the following steps: the method comprises the following steps of collecting auxiliary nozzle components → cleaning → detecting → matching → coping → assembling → testing the flow rate and the cone angle of the auxiliary nozzle before welding → coping the aperture of the auxiliary nozzle → soldering → sealing test of the auxiliary nozzle after welding → testing the flow rate and the cone angle of the auxiliary nozzle after welding → dissecting the test piece → marking → final inspection; vacuum brazing refers to brazing in which a weldment fitted with a brazing filler metal is placed in a vacuum environment and heated. The typical brazing filler metal for brazing titanium and titanium alloy comprises, by mass, 22-32% of Ni; 1-1.5% of Al; 0.5 to 1.0 percent of Mn; 0.3 to 0.6 percent of V; 0.6 to 1.0 percent of Sn; 1.5-2% of Zr; the balance being Cu (if necessary, a brazing material containing noble metals palladium and silver is selected). The brazing temperature is 945-1090 ℃, and the brazing time is 25-60 min. The raw materials are proportioned, smelted and poured into brazing alloy ingots, and then extruded and rolled into brazing foils. The brazing filler metal is vacuum-welded (or argon-shielded), and can be rolled into a foil strip of 0.02mm, and the brazing end face forms a mounting face and/or a contact face for connection.
In the figure, L1 +/-0.05 is in a detection process, the pieces 1, 2 and 3 meeting the design drawing requirements are placed in a bag set, and the right end face of the piece 1 which does not meet the design requirements is allowed to be repaired to meet the requirements.
The assembly parts 2 and 3 are tested through a flow tool to detect the flow and the cone angle of the auxiliary nozzle, and when the flow and the cone angle do not meet the requirements, a coping method is allowed to be adopted, and the requirements of the flow and the spray cone angle are met by changing the aperture of the auxiliary nozzle and the size of the swirl groove of the auxiliary swirler. And (4) debugging each nozzle one by one, but the outlet end face of the auxiliary nozzle cannot be polished in the adjusting process.
The second braze is shown in fig. 7: the processing flow comprises the following steps: parts 5, 6, 1-3 and 9 are integrated → cleaned → detected → selected and matched → assembled I → flow rate and spray angle test of the main nozzle before welding → repair grinding → assembled II → brazing → cleaned → gas seal test of the auxiliary nozzle after welding → gas seal test of the main nozzle after welding → liquid seal test of the auxiliary nozzle after welding → liquid seal test of the main nozzle after welding → flow rate and spray cone angle test of the auxiliary nozzle after welding → flow rate and spray cone angle test of the main nozzle after welding → air flow test of the primary swirler → mark → final inspection.
In the detection process, L1 +/-0.05 in the drawing is packaged and placed in a set by the parts 5, 6 and 1-3 assemblies meeting the requirements of the design drawing.
The piece 6 and the piece 9 are assembled by using a tool to test the flow rate and the spraying angle of a main nozzle before welding, when the requirements are not met, the size of the swirl groove of the piece 6 is allowed to be ground and adjusted until the size of the swirl groove meeting the performance requirements is obtained, and the swirl groove is matched and ready for use after grinding.
Electron beam welding is shown in fig. 8: the processing flow comprises the following steps: main nozzle outer tube (i.e., nozzle housing) assembly → cleaning → inspection → electron beam welding → X-ray inspection → fluoroscopy → final inspection. Electron beam welding, wherein the welding temperature is controlled to reach 1200-1400 ℃ by controlling the deflection rate of the power of the electron beam, namely the product of the beam current and the acceleration voltage, and the power of the electron beam is about 60 kW. The power of the beam spot (or focal point) of the electron beam can reach 106～108W/cm2。
And finishing the processing of the nozzle assembly by two times of brazing and one time of electron beam welding. Through the procedures of a gas seal test, a lubricating oil seal test, a welded main nozzle flow and auxiliary nozzle flow and spray cone angle test, a primary cyclone air flow test and a secondary cyclone air flow test and the like, the assembly meets the design target.
Claims (5)
1. The machining method of the fuel nozzle assembly of the aircraft engine comprises the following workpieces: the main oil way, the auxiliary nozzle adapter section, the main nozzle, the auxiliary nozzle, the adapter pipe, the rear cover plate, the first-stage swirler, the second-stage swirler and the nozzle shell; the first-stage swirler and the second-stage swirler are sleeve structures with gaps and are respectively sleeved on the auxiliary nozzle of the inner pipe of the concentric pipe and the end part of the nozzle shell; the main oil circuit and the auxiliary oil circuit are parallel pipelines at the inclined lower part, the parallel pipelines are bent into a main nozzle and an auxiliary nozzle of a horizontal concentric tube structure through an adapter tube, the adapter tube is a vertical tube and is connected to an inner tube of the horizontal concentric tube, the main nozzle and the auxiliary nozzle are characterized in that the contact surface of the outer tube end surface (which is connected to the main nozzle) of the concentric tube at the outer side of the adapter tube is a leakage-prone part, a brazing material groove is additionally arranged at the brazing position of the main nozzle, namely the outer tube of the concentric tube at the contact part of the main nozzle and the adapter tube, and the height and the width of the cross section of the groove are both 1-1.5 mm; forming a foil by using a brazing filler metal for titanium alloy brazing, folding and placing the foil in a brazing filler metal groove, wherein the width of the formed foil of the brazing filler metal is the width of the brazing filler metal groove, and then performing vacuum brazing; second stage swirler and nozzle shell use electron beam welding, and nozzle shell is 3D printing, second stage swirler and nozzle shell machine tooling: the inner cavity of the second-stage swirler is matched and concentric with the outer cavity end turning rabbet of the nozzle shell, and then the two parts of the second-stage swirler and the nozzle shell are welded by electron beams.
2. A method of machining an aircraft engine fuel nozzle assembly as claimed in claim 1, wherein the clearance of the workpiece is 0.03 to 0.05 mm; the gaps of the soldering points are filled with solder foil.
3. A method for manufacturing an aircraft engine fuel nozzle assembly according to claim 1, wherein the mating surface of the main nozzle and the nozzle housing is a welding surface, a brazing material groove is added to the welding surface, and the height and width of the cross section of the groove are both 1-1.5 mm; forming a foil by using a brazing filler metal for titanium alloy brazing, folding and placing the foil in a brazing filler metal groove, wherein the width of the formed foil of the brazing filler metal is the width of the brazing filler metal groove, and then performing vacuum brazing; the adapter tube bends into an outer tube main nozzle with a concentric tube structure.
4. The aircraft engine fuel nozzle assembly processing method according to claim 1, wherein the matching position of the end surface plane of the vertical pipe of the adapter pipe and the inner side surface of the outer pipe (namely the nozzle shell) of the main nozzle is also a brazing surface, a brazing groove is additionally arranged on the brazing surface, and the height and the width of the cross section of the groove are both 1-1.5 mm.
5. A method of fabricating an aircraft engine fuel nozzle assembly as defined in claim 1, wherein the first brazing: and (3) performing vacuum brazing after the secondary nozzle assembly is assembled, wherein the vacuum brazing refers to brazing performed by heating the weldment which is assembled with the brazing filler metal in a vacuum environment. The typical brazing filler metal for brazing titanium and titanium alloy comprises, by mass, 22-32% of Ni; 1-1.5% of Al; 0.5 to 1.0 percent of Mn; 0.3 to 0.6 percent of V; 0.6 to 1.0 percent of Sn; 1.5-2% of Zr; the balance being Cu (if necessary, a brazing material containing noble metals palladium and silver is selected). The raw materials are proportioned, smelted and cast into brazing ingot, and then extruded and rolled into brazing foil. The brazing solder adopts vacuum welding (argon protection is also available), can be rolled into a foil strip with the thickness of 0.02mm, and the brazing end face forms a mounting face and/or a contact face for connection;
and (3) second brazing: the parts 5 and 6, the parts 1-3 and the part 9 are integrally brazed;
the piece 6 and the piece 9 are assembled and are tested by using a tool before welding for the flow and the spraying angle of a main nozzle, when the flow and the spraying angle of the main nozzle do not meet the requirements, the size of the swirl groove of the piece 6 is allowed to be ground and adjusted until the size of the swirl groove meeting the performance requirements is obtained, and the swirl groove is matched and ready for use after grinding;
electron beam welding: and electron beam welding is carried out on the outer pipe of the main nozzle, namely the nozzle shell assembly.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210390816.4A CN114571117A (en) | 2022-04-14 | 2022-04-14 | Machining method for fuel nozzle assembly of aircraft engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210390816.4A CN114571117A (en) | 2022-04-14 | 2022-04-14 | Machining method for fuel nozzle assembly of aircraft engine |
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| Publication Number | Publication Date |
|---|---|
| CN114571117A true CN114571117A (en) | 2022-06-03 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210390816.4A Pending CN114571117A (en) | 2022-04-14 | 2022-04-14 | Machining method for fuel nozzle assembly of aircraft engine |
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20100096037A1 (en) * | 2008-10-16 | 2010-04-22 | Woodward Governor Company | Multi-Tubular Fluid Transfer Conduit |
| CN103375817A (en) * | 2012-04-30 | 2013-10-30 | 通用电气公司 | A fuel nozzle |
| CN104097008A (en) * | 2014-07-15 | 2014-10-15 | 中国南方航空工业(集团)有限公司 | Fixing fixture and machining method for fuel spray nozzles |
| CN211524959U (en) * | 2020-01-19 | 2020-09-18 | 中国航发上海商用航空发动机制造有限责任公司 | Precise pipeline containing inner nested pipe and aircraft engine fuel nozzle thereof |
-
2022
- 2022-04-14 CN CN202210390816.4A patent/CN114571117A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20100096037A1 (en) * | 2008-10-16 | 2010-04-22 | Woodward Governor Company | Multi-Tubular Fluid Transfer Conduit |
| CN103375817A (en) * | 2012-04-30 | 2013-10-30 | 通用电气公司 | A fuel nozzle |
| CN104097008A (en) * | 2014-07-15 | 2014-10-15 | 中国南方航空工业(集团)有限公司 | Fixing fixture and machining method for fuel spray nozzles |
| CN211524959U (en) * | 2020-01-19 | 2020-09-18 | 中国航发上海商用航空发动机制造有限责任公司 | Precise pipeline containing inner nested pipe and aircraft engine fuel nozzle thereof |
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