EP0915180B1 - Verfahren zur Verbesserung der Haftstärke zwischen wiederstandgeschweisste Gegenstände aus Titan-Legierung - Google Patents

Verfahren zur Verbesserung der Haftstärke zwischen wiederstandgeschweisste Gegenstände aus Titan-Legierung Download PDF

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Publication number
EP0915180B1
EP0915180B1 EP19970117489 EP97117489A EP0915180B1 EP 0915180 B1 EP0915180 B1 EP 0915180B1 EP 19970117489 EP19970117489 EP 19970117489 EP 97117489 A EP97117489 A EP 97117489A EP 0915180 B1 EP0915180 B1 EP 0915180B1
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European Patent Office
Prior art keywords
titanium alloy
articles
hours
resistance welding
heat treating
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Expired - Lifetime
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EP19970117489
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English (en)
French (fr)
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EP0915180A1 (de
Inventor
Sami M. El-Soudani
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Boeing Co
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Boeing North American Inc
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Priority to ES97117489T priority Critical patent/ES2188844T3/es
Priority to DE1997618648 priority patent/DE69718648T2/de
Priority to EP19970117489 priority patent/EP0915180B1/de
Publication of EP0915180A1 publication Critical patent/EP0915180A1/de
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    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • C22F1/16—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of other metals or alloys based thereon
    • C22F1/18—High-melting or refractory metals or alloys based thereon
    • C22F1/183—High-melting or refractory metals or alloys based thereon of titanium or alloys based thereon

Definitions

  • the present invention relates to methods for processing titanium alloys and, more particularly, to a process for enhancing the bond strength of a metallurgical joint between two titanium alloy articles.
  • HSCT high speed civil transport
  • HSCT emphasis is on the use of titanium alloys because, under Mach 2.4 conditions, they exhibit damage tolerance and durability, as well as thermal stability, required for the expected 72,000 hours at supersonic cruise temperatures of about 177,67°C (350°F) throughout one airplane lifetime. At such temperatures, virtually all heat treatable ( below, frequently temperatures are given in °F.
  • Enhancement of titanium alloy properties has been achieved in the process disclosed and claimed in U. S. Patent Serial No. 08/339,856, entitled "A Method for Processing-Microstructure-Property Optimization of Alpha-Beta Titanium Alloys to Obtain Simultaneous Improvements in Mechanical Properties and Fracture Resistance", assigned to Rockwell International Corporation.
  • Resistance welded honeycomb titanium alloy structures are known in the field. However, they tend to exhibit lower flatwise tension strength in comparison with other joining methods, e.g. aluminum brazed honeycomb or transient liquid phase bonding. Post-weld thermal processing is important. As will be disclosed below, the present patent application describes an improved processing sequence in this field.
  • Another object of the present invention is to provide an efficient joining of face sheets to a honeycomb core element with improved balance of strength properties of the face sheets and the core element.
  • the present invention provides the above-mentioned improved thermal processing parameters for joint enhancement in titanium alloys after resistance welding.
  • the present Applicant has found that, in the specified temperature range and period of time, the interdiffusion of joint materials takes place at such higher rates as to provide enhanced homogeneous bond interface microstructures, which, in turn, provide for higher interface bond strength. Surprisingly, such high temperatures are required to eliminate interfacial oxide layers and other defective microstructures.
  • Figure 1 is an exploded perspective view of portions of typical articles being metallurgically joined by the process of the present invention.
  • Figure 2 is a block schematic diagram of the fabrication processing sequence for joint enhancement while transforming titanium alloy article microstructures from ⁇ + ⁇ to ⁇ + ⁇ 2 + ⁇ .
  • Figure 3 is a block diagram of the fabrication processing sequence for joint enhancement while retaining/regenerating the ⁇ + ⁇ 2 + ⁇ microstructure.
  • Figure 4 is a micrograph of a typical metallurgical bond joint (resistance spot weld) in accordance with the principles of the first step of the present invention.
  • Figure 5 is a micrograph showing a deficient bond interface between a Ti 6242S face sheet and Beta 21S honeycomb core resulting from a conventional relatively low temperature heat treatment (1625°F heat treatment for 2 hours).
  • Figure 6 is a micrograph showing a bond interface between a Ti 6242S face sheet and a Beta 21S honeycomb core resulting from processing in accordance with the principles of the present invention (1800°F heat treatment for 2 hours).
  • Figure 7 is a graph of flatwise tension strength as a function of post-weld processing temperatures and hold times for various test specimens illustrating the respective strength property scatter bands of bond joints.
  • Figure 8 is a graph of flatwise tension strength as a function of post weld processing methods, showing the superior bond enhancement of the present invention both at face-sheet-to-core joint and core-to-core joint.
  • Figures 9a-d are block diagrams illustrating the fabrication processing sequence of the present invention, as applied to various alpha/beta titanium alloy systems.
  • Figure 1 shows two titanium alloy face sheets 10, 12, which are to be joined to a titanium alloy honeycomb core element 14.
  • the face sheets 10, 12 may be formed of, for example, alpha-beta titanium alloys.
  • the titanium alloy articles may be near alpha or beta alloys.
  • the principles of the present invention, as will be disclosed below, are particularly advantageous with the use of a honeycomb core element 14.
  • Honeycomb core elements are particularly advantageous because they provide the capability of greater weight reductions for the same structural stiffness. Such honeycomb core structures and other stiffened structures are commonly used in the construction of aircraft.
  • FIG. 1 a block schematic diagram of the fabrication processing sequence for joint enhancement, while transforming titanium alloy article microstructures from ⁇ + ⁇ to ⁇ + ⁇ 2 + ⁇ is illustrated, designated generally as 16.
  • Two titanium alloy articles having ⁇ + ⁇ microstructures 18 are resistance welded.
  • the resistance welding technique is well know in this field. In the resistance welding technique two materials are brought together under pressure and large electrical currents are applied through the contact interface between the two articles. As a result of electrical resistance heating at the contact interface, a small weld nugget of molten metal is formed, thus achieving the bond upon its solidification.
  • This step of resistance welding may be applied in different configurations by spot welds or continuous seem welds.
  • the ⁇ + ⁇ microstructure is maintained, even after resistance welding, as shown by block 20.
  • the bonded materials are brought together in contact, which extends over areas outside the molten weld nuggets.
  • the articles are then heat treated at temperatures in a range of 1675°F to 1825°F for a period of 15 minutes to 4 hours to further bond additional contact areas brought together by the shrinkage stresses exerted by the resistance weld.
  • This heat treatment step also converts the ⁇ + ⁇ microstructure to an ⁇ + ⁇ 2 + ⁇ microstructure as shown by block 22.
  • the heat treatment be in a range of between about 1700°F and 1800°F for a period of 1-3 hours.
  • the heat treatment step discussed herein is provided in a vacuum or inert environment, preferably a vacuum environment. (If an inert environment is used, it should be pure argon or helium.)
  • FIG. 3 the processing techniques of the present invention are illustrated, as applied to titanium alloy articles having ⁇ + ⁇ 2 + ⁇ microstructures initially, as designated generally by 24.
  • the ⁇ + ⁇ 2 + ⁇ titanium alloy articles 26 are resistance welded as discussed above in the previous embodiment.
  • the ⁇ + ⁇ 2 + ⁇ microstructure is preserved, as shown by numeral designation 28.
  • the joined articles are then heat treated. It is understood that the ⁇ + ⁇ 2 + ⁇ microstructure is retained in the bonded articles with the exception of the weld nugget, which may be ⁇ + ⁇ .
  • the heat treatment temperature ranges and time periods are as discussed above with respect to the Figure 2 embodiment.
  • the ⁇ + ⁇ 2 + ⁇ microstructure is preserved/regenerated after heat treatment, as shown by block 30.
  • FIG 4 a micrograph of a typical resistance spot welded metallurgical bond joint is illustrated, in accordance with the principles of the first step of the present process.
  • This bond joint designated generally as 32.
  • the materials joined in Figure 4 are a Ti 6242S face sheet 34 and a honeycomb core of Beta 21S alloy, designated by numeral designation 36.
  • the micrograph shows a weld nugget of molten metal 38 adjacent to a contact surface 40.
  • Figure 5 shows a cross section of the contact surface following post-weld thermal processing at an undesirably low subsequent heat treatment processing temperature of 1625°F, for two hours.
  • the interface morphology is substantially the same as the interface 40 of the solely resistance spot welded sample of Figure 4.
  • Figure 6 illustrates the advantages of the higher temperature heat treatment of the present invention.
  • the articles were heated to 1800°F for two hours.
  • the interface morphology comprises a very broad domain of diffusion with mutually attractive phases. This substantially increases the bond strength of the joint.
  • Figure 7 illustrates the results of mechanical tests comprised of flatwise tension testing of small honeycomb elements excised from honeycomb elements processed in accordance with methods discussed above with respect to Figures 5 and 6.
  • reference to "Conventional Processing” means processing described above with respect to Figure 5, that is at 1625°F heat treatments.
  • Reference to "Present Invention Improved Processing” means heat treatments in accordance with the discussion of Figure 6 of the present invention (1800°F heat treatment for two hours).
  • the flatwise tension test is a well known method in evaluating the strength of honeycomb sandwiches. It consists of bonding pull bar elements to the faces of a honeycomb segment measuring about 2 x 2 inches. In this test, the tensile forces are thus directed to separate the face sheets from the core element in a direction normal to the face sheet.
  • the process of the present invention provides a substantial increase in the strength of the face sheet to core bond joint strength. This is due to the improved interface diffusion illustrated in Figure 6 as compared to the prior art Figure 5.
  • the left side of the graph presents the average values of the measured flatwise tension strength test results shown in Figure 7.
  • the right side of Figure 8 shows a comparison of the associated core node bond strength.
  • the nodes were prepared by resistance spot welding similar to that illustrated in Figure 4.
  • the strength enhancement of the core node bond is due to the same effects, which improved the face sheet to core bond joint.
  • the present invention preferably includes a step of cooling the titanium alloy articles after the step of heat treating discussed above, and then aging the articles at a temperature in a range of about 850°F to 1150°F for a period of about 8 hours to 24 hours to prevent silicide precipitation.
  • the step of aging preferably comprises aging the articles at a temperature of about 1100°F. It is understood that the step of cooling comprises cooling in a protective environment. This step of cooling is preferably conducted at a cooling rate in a range of 5°F per minute to 500°F per minute.
  • the process of the present invention does not require such a complicating process application.
  • the bonded surfaces outside the weld zone are brought together in solid contact by the shrinkage stresses of the resistance welds in the absence of the external mechanical forces acting on the titanium alloy articles.
  • Figures 9a-d illustrates various other alpha/beta titanium alloy systems which may utilize the principles of the present invention.

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  • Chemical & Material Sciences (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Pressure Welding/Diffusion-Bonding (AREA)
  • Arc Welding In General (AREA)
  • Professional, Industrial, Or Sporting Protective Garments (AREA)

Claims (11)

  1. Verfahren zur Verbesserung der Haftstärke einer metallurgischen Verbindung zwischen zwei Titanlegierungsgegenständen, wobei die folgenden Schritte vorgesehen sind:
    a) Widerstandsschweißen von zwei Titanlegierungsgegenständen; und
    b) Wärmebehandlung der widerstandsgeschweißten Titanlegierungsgegenstände in einem Vakuum oder in einer inerten Umgebung bei Temperaturen im Bereich von 912.78°C (1675°F) bis 996.11°C (1825°F) für eine Zeitdauer von 15 Minuten bis 4 Stunden, wobei das Verfahren in Abwesenheit von irgendwelchen substantiellen externen mechanischen Kräften ausgeführt wird, vorgesehen zur Verbesserung der metallurgischen Verbindung zwischen den Titanlegierungsgegenständen.
  2. Verfahren nach Anspruch 1, wobei der Schritt des Widerstandsschweißens das Widerstandsschweißen einer Wabenkernstruktur mit einem Stirnblech umfaßt.
  3. Verfahren nach Anspruch 1, wobei der Schritt des Widerstandsschweißens das Widerstandsschweißen von α + β Titanlegierungsgegenständen umfaßt und wobei der Schritt der Wärmebehandlung die Wärmebehandlung im Bereich von 926.67 °C (1700°F) bis 982.22°C (1800°F) umfaßt , und zwar für eine Zeitperiode von 1-3 Stunden.
  4. Verfahren nach Anspruch 1, wobei der Schritt des Widerstandsschweißens folgendes umfaßt:
    Widerstandsschweißen von mindestens einem α + β Titanlegierungsgegenstand an einen zweiten Titanlegierungsgegenstand; und
       wobei der Schritt der Wärmebehandlung die Wärmebehandlung in einem Bereich von zwischen 926.67°C bis 982.22°C (1700°F - 1800°F) für eine Zeitdauer von 1-3 Stunden umfaßt, um den erwähnten mindestens einen α + β Titanlegierungsgegenstand in einem α + α2 + β Titanlegierungsgegenstand umzuwandeln.
  5. Verfahren nach Anspruch 4, wobei der zweite Titanlegierungsgegenstand auch eine α + β Microstruktur besitzt.
  6. Verfahren nach Anspruch 1, wobei der Schritt des Widerstandsschweißens folgendes umfaßt:
    Widerstandsschweißen von mindestens einem α + α2 + β Titanlegierungsgegenstand an einen Titanlegierungsgegenstand; und
       wobei der Schritt der Wärmebehandlung die Wärmebehandlung in einem Bereich von zwischen 926.67 °C und 982.22°C (1700°F und 1800°F) für eine Zeitperiode von 1-3 Stunden umfaßt.
  7. Verfahren nach Anspruch 1, wobei der erwähnte zweite Titanlegierungsgegenstand ebenfalls eine α + α2 + β Microstruktur besitzt.
  8. Verfahren nach Anspruch 1, wobei der Schritt der Wärmebehandlung in einer Vakuumumgebung ausgeführt wird.
  9. Verfahren nach Anspruch 1, wobei ein Schritt des Kühlens der Titanlegierungsgegenstände vorgesehen ist, und zwar nach dem Schritt der Wärmebehandlung und sodann die Alterung der Gegenstände bei einer Temperatur in einem Bereich von ungefähr 454.44 °C bis 621.11°C (850°F bis 1150°F) für eine Zeitdauer von ungefähr 8 Stunden bis 24 Stunden, um die Silicidausscheidung zu verhindern.
  10. Verfahren nach Anspruch 9 (10), wobei der Schritt der Alterung die Alterung der erwähnten Gegenstände bei einer Temperatur von ungefähr 593.33°C (1100°F) umfaßt.
  11. Verfahren zur Verbesserung der Verbindungsfestigkeit oder Haftstärke einer metallurgischen Verbindung zwischen zwei Titanlegierungsgegenständen, wobei die folgenden Schritte vorgesehen sind:
    a) Widerstandsschweißen von zwei Titanlegierungsgegenständen;
    b) Wärmebehandlung der widerstandsgeschweißten Titanlegierungsgegenstände in einem Vakuum oder in einer inerten Umgebung bei Temperaturen in einem Bereich von 912.78°C bis 996.11°C (1675°F bis 1825°F) für eine Zeitdauer von 15 Minuten bis 4 Stunden, wobei das Verfahren ausgeführt wird bei Nichtanwesenheit von irgendwelchen substantiellen externen mechanischen Kräften beabsichtigt zur Verbesserung oder Erhöhung der metallurgischen Verbindung zwischen den Titanlegierungsgegenständen;
    c) Kühlen der Titanlegierungsgegenstände; und
    d) Alterung der Gegenstände bei einer Temperatur im Bereich von 454.44°C bis 621.11°C (850°F bis 1150°F) für eine Zeitdauer von 8 Stunden bis 24 Stunden.
EP19970117489 1997-10-09 1997-10-09 Verfahren zur Verbesserung der Haftstärke zwischen wiederstandgeschweisste Gegenstände aus Titan-Legierung Expired - Lifetime EP0915180B1 (de)

Priority Applications (3)

Application Number Priority Date Filing Date Title
ES97117489T ES2188844T3 (es) 1997-10-09 1997-10-09 Procedimiento para aumentar la resistencia de union de juntas soldadas entre articulos de aleacion de titanio.
DE1997618648 DE69718648T2 (de) 1997-10-09 1997-10-09 Verfahren zur Verbesserung der Haftstärke zwischen wiederstandgeschweisste Gegenstände aus Titan-Legierung
EP19970117489 EP0915180B1 (de) 1997-10-09 1997-10-09 Verfahren zur Verbesserung der Haftstärke zwischen wiederstandgeschweisste Gegenstände aus Titan-Legierung

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EP19970117489 EP0915180B1 (de) 1997-10-09 1997-10-09 Verfahren zur Verbesserung der Haftstärke zwischen wiederstandgeschweisste Gegenstände aus Titan-Legierung

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CN104400202B (zh) * 2014-10-27 2016-10-05 四川成发航空科技股份有限公司 适用于小直径蜂窝密封装配电阻定位焊限位工装
FR3106290B1 (fr) * 2019-09-09 2022-01-14 Safran Nacelles Panneau structural et/ou acoustique pour ensemble propulsif d’aéronef
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EP0915180A1 (de) 1999-05-12

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