Lambda Technologies Events

Event Schedule for 2008-2009

Look for Lambda Technologies participation in these future events:

ASIP 2008

ASIP provides a forum for the technical interchange of information between personnel responsible for structural integrity, including design, analysis, testing, manufacture, certification, non-destructive evaluation/inspection, maintenance, repair, safety, risk assessment and mitigation, durability and life management. This interchange helps provide the communication necessary to ensure that each community is aware of each other's capabilities and needs. This conference has become even more important to the Air Force, Navy, Army, NASA and the FAA due to the constantly growing emphasis on sustaining the airworthiness of aging aircraft. This conference is unclassified and allows unlimited attendance. It has become internationally recognized as the premier meeting for this technical area, in the world. Consequently, a large number of well-qualified foreign nationals attend the conference, and bring a very broad perspective to the technology being discussed.

ICSP 10 - Event Highlights

(Excerpt from Abstract) Corrosion fatigue, stress corrosion cracking and high cycle fatigue initiating from corrosion pits are primary failure mechanisms that reduce the structural integrity of aircraft. A chemically active environment, susceptible material and either static or alternating tensile stresses are required for failure. Conventional approaches to mitigate corrosion related failure mechanisms in aircraft usually involve isolation from the corrosive environment via protective coatings, alloy substitution or modifications in design to reduce stresses, all expensive solutions. This paper describes an alternate approach employing surface enhancement by low plasticity burnishing (LPB) to eliminate or reduce the surface tensile stresses necessary for corrosion fatigue failure in AA7475-T7351 and AA2024-T351, without alteration of environment, material or component design. (See the entire abstract)

F-16/Proven Aircraft World Wide Review (WWR) - Event Highlights

Building on previous successful events, the 3rd annual F-16/Proven Aircraft Worldwide Review (WWR) aimed to foster international exchange and friendship in the pursuit of supporting military weapon systems around the world. The WWR serves as a platform for contractors, US Government and International Partners to present the latest technologies, upgrades and offer services for aircraft sustainment. The conference offered keynote speakers to highlight some of the major developments within the systems. Lambda was pleased to participate as an exhibitor at the event. Thanks to all who visited us at Booth No. 87.

TETS 2008 - Event Highlights

The Turbine Engine Technology Symposium is the only forum where the United States’ turbine engine community gathers to review and discuss the latest technology advances achieved through the Versatile, Affordable, Advanced Turbine Engines (VAATE) Program. Comprised of all sectors of the Department of Defense, NASA, the Department of Energy, six major engine companies and three airframe manufacturers, VAATE is a totally integrated, physics-based, turbine engine technology program chaired by the Office of the Secretary of Defense. VAATE’s mission is to develop, demonstrate and transition advanced, multi-use, turbine engine technologies that provide a revolutionary improvement in affordable capability to a broad range of legacy, emerging and future propulsion and power needs, with explicit versatility for dual use application.

Lambda Technologies was proud to participate in the 2008 Turbine Engine Technology Symposium in Dayton. Thanks to all who stopped by our booth. We look forward to TETS 2010.

AeroMat 2008 - Event Highlights

(Excerpt from Abstract) Use of compressive residual stresses in turbine engine compressor parts is proving to be very useful for sustainment of parts prone to different damage conditions. The leading and trailing edge of blades and vanes are subject to fatigue cracking and foreign object damage (FOD). Both the blade dovetail and the rotor disk post contact surfaces are vulnerable to fretting damage, which leads to microcracking and mode I fatigue cracks. Low plasticity burnishing (LPB) has been shown to introduce controlled magnitude and distribution of compressive residual stresses to completely mitigate either FOD on the edges of vanes and blades or fretting-induced microcracks at the edge of bedding on the contact faces of the dovetails and rotor disk posts.
(See the entire abstract)

F-16 ASIP Review 2008 - Event Highlights

As an invited participant, Lambda Technologies exhibited at the 2008 F-16 ASIP Review located at the Lockheed Martin (LMRA) Facilities in Fort Worth, TX. Technical presentations from suppliers, users and Lockheed Martin Aero staff covering process overviews, Non-destructive inspection (NDI), repair/life extension, and structural analysis took place at the F16 ASIP Review in addition to the supplier trade show and conference general session. We were pleased to meet our fellow F-16 ASIP contractors in Fort Worth.

18th Summer PEWG Technical Training Meeting - Event Highlights

The Propulsion Environmental Working Group (PEWG) is an Air Force military service and industry partnership with a mission to work within the military propulsion community to discover and insert safe, clean, and effective manufacturing, maintenance, repair and overhaul (MRO) technologies to improve process & product sustainment, performance, affordability and competitiveness with foreign technology. This year, the PEWG conference focused on project management reviews for our joint programs, training on new start technologies and out-year (FY09-11) project forecasting.

Dr. N. “Jay” Jayaraman of Lambda Technologies showcased Low Plasticity Burnishing (LPB) on Wednesday, June 18, 2008. Also, Dr. Jayaraman spoke at the “Coatings” session held Monday, June 16. To our colleagues in the military propulsion community, we were pleased to visit with you in Oklahoma City.

ICONE 16 - Event Highlights

(Excerpt from Paper) Stress corrosion cracking (SCC) has been observed for decades in austenitic alloy weldments such as type 304 stainless steel as well as in Ni based alloy weldments including Alloy 600 and 690. SCC continues to be a primary maintenance concern for many components in both pressurized water reactors (PWR) and boiling water reactors (BWR). SCC is understood to be the result of a combination of susceptible material, exposure to a corrosive environment, and tensile stress above a threshold. Tensile residual stresses developed by prior machining and welding can accelerate SCC. A surface treatment is needed that can reliably produce deep compressive residual stresses in austenitic and Ni based alloy weldments in order to prevent SCC.

Post-weld surface enhancement processing via low plasticity burnishing (LPB) can be used to introduce deep compression into tensile fusion welds thereby mitigating SCC. LPB has been developed as a rapid and inexpensive surface enhancement method adaptable to existing CNC machine tools or robots. Deep compressive residual stresses produced by LPB are designed to reduce the surface, and near surface stress state to well below the SCC threshold. Residual stress results are shown for 304 stainless steel, Alloy 22 and Alloy 718. SCC test results comparing LPB treated and un-treated 304 stainless steel weldments are presented. Results show that the deep compression produced by LPB eliminates SCC in austenitic weldments. (See the paper )

Aging Aircraft 2008 - Event Highlights

As it has proven in the past, Aging Aircraft was a successful event for the attending staff of Lambda Technologies. In addition to Dr. Jayaraman's presentation (below), Lambda's participation in Aging Aircraft was enhanced by a rewarding exhibition sesssion in which we were happy to meet many commercial and miltary contractors and engineers who are interested in improving component performance via the incorporation of compressive residual stress. We look forward to Aging Aircraft 2009 in Kansas City next May!

(Technical Paper Abstract) A test program was set up by AFRL-VASM to study the effect of low plasticity burnishing (LPB) to mitigate fatigue debit due to pre-cracking damage in two feature specimens made of AA2024-T851 and designed to simulate features of aircraft structures. The LPB solution consisted of (a) designing the compressive residual stress field using Lambda’s Fatigue Design Diagram (FDD) method, (b) introducing the compression via LPB tools and fixtures into the parts, (c) verifying the achieved residual stress distribution by measurements, and (d) validating the predictions through fatigue tests conducted by AFRL-VASM group. (See the entire technical paper )

MRO 2008 - Event Highlights

The Lambda Technologies staff would like to thank those MRO 2008 attendees who stopped by our booth to see how Low Plasticity Burnishing (LPB) is positioned to influence the MRO industry. Our team was also pleased to personally meet many of our fellow exhibitors. We look forward to participating as an exhibitor at MRO 2009. MRO professionals who have interest in reducing landing gear, engine and structures maintenance costs while improving overall component performance will greatly benefit from a visit to our booth (No. 944) next year in Dallas.

P-SAR 2008 - Event Highlights

The Third Annual Propulsion - Safety and Affordable Readiness (P-SAR) Program Review highlighted recent advanced technologies that will have significant impact on propulsion system safety and affordable readiness. Lambda Technologies has a history of supporting the P-SAR event each year and we look forward to participating in future P-SAR events.

(Excerpt from Abstract) Fretting damage on the contact surfaces of blade dovetail regions is a common cause of fatigue initiation in titanium alloy compressor blades and disks. Fatigue cracks usually initiate at the edge of the blade-disk contact zone, or edge of contact. The slight relative motion of the surfaces under high contact pressure creates alternating shear stresses that can be sufficient to initiate small micro-cracks in shear (Mode II) that grow only to the shallow depth of the shear stress distribution, typically less than 0.005 in. Catastrophic engine failure results from the propagation of the fretting induced shear cracks in Mode I under the tensile normal stresses developed in service. (See the entire abstract)

TMS 2008 - Event Highlights

Dr. N. "Jay" Jayaraman, Director of Materials Research for Lambda Technologies presented "Fatigue Design Diagram (FDD) Code to Design Compressive Residual Stresses to Improve Performance of Damage-Limited Components and Structures", at TMS 2008.

(Technical Paper Abstract) The Fatigue Design Diagram (FDD) is mainly used to design residual stresses (RS) to mitigate different damage conditions. It is also designed to take credit for beneficial residual stresses in components to achieve a required or optimal fatigue performance. The FDD code has been developed to interact with commercial finite element analysis (FEA) codes to determine the required residual stress distribution in a component or structure. Design features include determination of minimum, maximum and optimum residual stress distribution for fixed mean stress condition and fixed stress-ratio (R = Smin/Smax) condition. Other analytical features like prediction of fatigue life in the presence of known residual stress distributions will also be discussed. In this paper, the progress made to date on the use of the FDD Code will be described. The paper will demonstrate the coupling of the FDD code with other standard commercial analytical tools with specific examples. (See the entire technical paper)