Turbine Engine Structural Integrity Program /ENSIP/

Cowie, W.

doi:10.2514/3.44457

Cited by 9 publications

(4 citation statements)

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“…LSP is a novel industrial process by which metals are treated with high energy‐pulsed laser beam that leads to deep compressive residual stresses an near‐surface microstructural changes. The process was initially developed in the aerospace industry to improve the strength of rapidly rotating aircraft engine blades in jet engines (Clauer and Lahrman, 2001; Clauer et al , 2004; Cowie et al , 1997; Mannava et al , 1996, 1997; Mannava and Rockstroh, 2005; Montross et al , 2002; Nalla et al , 2003; Ruschau et al , 1999; Thompson et al , 1996).…”

Section: The Approachmentioning

confidence: 99%

Application of laser shock peening for spinal implant rods

Mannava

Bhamare

Chaswal

et al. 2011

International Journal of Structural Integrity

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PurposeThe current industry standard rigid spinal implants suffer fatigue failures due to bending and torsion loads. The purpose of this program was to design novel prototype flexible titanium alloy spinal implant rod with machined features, and then apply the laser shock peening (LSP) process to restore the fatigue strength debit due to these features.Design/methodology/approachA flexible prototype rod was designed with flat section at the center of the rod. The flat section was laser shock peened. Static compression tests were conducted as per American Society of Testing Materials standards for three‐ and four‐point bending tests and “vertebrectomy” constructs. Finite element models were developed to aid in the design of LSP and also to guide the experiments.FindingsThe test results indicated a ∼3X improvement in flexibility and a reduction in fatigue load ratio, defined as applied load divided by the yield load; from 72 to 68 percent. This rod was LSP's on the flat sections, and tested again. The results indicated an increase in the fatigue load ratio from 68 to 75 percent without any further change in flexibility.Originality/valueIt has been demonstrated successfully that the current industry rigid spinal implant rod can be modified for flexibility and laser shock peened to increase fatigue strength. This enhancement will enable the use of the implant for longer periods and higher loads; and for surgical processes with and without fusion. This technology can be readily applied to all metals that are certified for human implant applications; thus can be implemented with minimal clinical trials.

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Section: The Approachmentioning

confidence: 99%

Application of laser shock peening for spinal implant rods

Mannava

Bhamare

Chaswal

et al. 2011

International Journal of Structural Integrity

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“…Turbine blade is a durability‐critical component of an aero‐engine whose failure will result in significant maintenance burden, but will not impair flight safety or mission completion 1 . Unlike the fracture‐critical component, durability‐critical components mainly influence the cost of ownership.…”

Section: Introductionmentioning

confidence: 99%

Experimental investigation on creep‐fatigue behaviours of as‐received and service‐exposed turbine blades: Mechanism and life evaluation

Shi

Yang

et al. 2020

Fatigue Fract Eng Mat Struct

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In the present study, both the as-received and the 600-h-serviced turbine blades were tested under the creep-fatigue loading. The results showed that the service-exposed blades exhibited a longer creep-fatigue life than the asreceived ones due to the refinement of grain size and the increasing of hardness during the service process. Micro structural characterization revealed that there was no directional coarsening or rafting of γ 0 precipitate after 600 h of service. Moreover, the as-received blades exhibited initial cyclic hardening followed by saturation and softening, whereas the 600-h-serviced blades only exhibited continuous softening until fracture. A conservative service life prediction approach was proposed considering the experienced mission profile. This service life estimation method provides a new way to assess the durability of turbine blade.

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“…The Turbine Engine Structural Integrity Program (ENSIP) was established by the US Air Force to provide the framework from which an engine contractor can derive a well-ordered structural development program to meet Air Force needs. [2] ENSIP provides a unifying approach to the engine structural development process through four basic program elements: structural design criteria, structural test requirements, structural data requirements, life monitoring requirements. More durable engines meet the Air Force mission requirements based on the guidance of ENSIP.…”

Section: Introductionmentioning

confidence: 99%

Durability Airworthiness Verification Connotation Analysis and Compliance Method Investigation for Turbine Blade

Shi

et al. 2019

KEM

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The durability airworthiness verification of turbine blade is one key issue in the process of certifying a type certificate for the aircraft engine. This paper summarizes the limiting factors for turbine blade durability and proposes a compliance method to evaluate the durability life of turbine blade. The typical standards of blade durability were selected and evolution history of the regulations was traced. The regulation contents and differences between CCAR-33 and CS-E were analyzed. A series of compliance methods in airworthiness verification process were discussed in detail. Furthermore, an experimental compliance methodology was proposed to estimate the durability life of turbine blade, considering the damage of creep and fatigue. The novel methodology was verified using the scanning electron microscope (SEM) analysis. These efforts are of great benefit to support the process of obtaining the final type certificate.

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Turbine Engine Structural Integrity Program /ENSIP/

Cited by 9 publications

References 0 publications

Application of laser shock peening for spinal implant rods

Application of laser shock peening for spinal implant rods

Experimental investigation on creep‐fatigue behaviours of as‐received and service‐exposed turbine blades: Mechanism and life evaluation

Durability Airworthiness Verification Connotation Analysis and Compliance Method Investigation for Turbine Blade

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