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Viewing 1 to 30 of 3482
2017-09-19
Technical Paper
2017-01-2045
Shivam Mishra, Sanjay Y
Gas turbine air-film blade cooling is widely used aero-derivative gas turbine blade cooling technique. The present paper reviews previously developed air-film blade cooling models. The article further proposes a new blade cooling model for estimating blade coolant mass fraction which takes into account the effect of radiative heat transfer from hot flue gases to aero-derivative gas turbine blade surface. Various possibilities to achieve enhanced performance from aero-derivative gas turbine have been enumerated namely effect of advanced design philosophies, thermal barrier coatings, advancement in blade material. Also adoption of advanced design philosophies such as 3-D CFD would lead to improved component design. Further use of advanced blade material specifically for gas turbine blade application including single-crystal blade, directionally solidified blade material being nickel-chrome-molybdenum alloys may be explored.
2017-09-19
Technical Paper
2017-01-2062
Tushar Choudhary, Mithilesh Sahu, Shreya KRISHNA
Solid oxide fuel cell (SOFC) is the most promising candidate for utilization of waste generated from the GT based power system. By coupling SOFC with gas turbine (GT) based power system, a hybrid SOFC–GT power system has been developed and the thermal efficiency of the system can be enhanced upto 70-85%. This paper focuses of thermodynamic analysis of an internal reformed solid oxide fuel cell which is integrated with the gas turbine cycle to form a hybrid power generation system for an unmanned aerial vehicle (UAV) with a long range. Thermodynamic 1st and 2nd law, parametric analysis has been carried out and the effect of various parameters such as compressor pressure ratio, turbine inlet temperature, air flow rate has been examined. In order to validate the results, present work has been compared with the available literature and it shows good agreement.
CURRENT
2017-08-04
Standard
AS5780C
This specification defines basic physical, chemical, and performance limits for 5 cSt grades of gas turbine engine lubricating oils used in aero and aero-derived marine and industrial applications, along with standard test methods and requirements for laboratories performing them. It also defines the quality control requirements to assure batch conformance and materials traceability, and the procedures to manage and communicate changes in oil formulation and brand. This specification invokes the Performance Review Institute (PRI) product qualification process. Requests for submittal information may be made to the PRI at the address in Appendix D Section D.2, referencing this specification. Products qualified to this specification are listed on a Qualified Products List (QPL) managed by the PRI. Additional tests and evaluations may be required by individual equipment builders before an oil is approved for use in their equipment.
CURRENT
2017-07-19
Standard
AIR4174A
The purpose of this SAE Aerospace Information Report (AIR) is to provide management, designers, and operators with information to assist them to decide what type of power train monitoring they desire. This document is to provide assistance in optimizing system complexity, performance and cost effectiveness. This document covers all power train elements from the point at which the gas generator energy is transferred to mechanical energy for propulsion purposes. The document covers engine power train components, their interfaces, transmissions, gearboxes, hanger bearings, shafting and associated rotating accessories, propellers and rotor systems as shown in Figure 1. This document addresses application for rotorcraft, turboprop, and propfan drive trains for both commercial and military aircraft. Information is provided to assist in; a. Defining technology maturity and application risk b. Cost benefit analysis (Value analysis) c. Selection of system components d.
2017-07-17
WIP Standard
AS7473C
This procurement specification covers bolts and screws made from carbon steels, high expansion steels, or corrosion and heat resistant steels of the type identified under the Unified Numbering System as follows: a. UNS K00802 - carbon steel (AMS 5061) b. UNS K91505 - high expansion steel (AMS 5624) c. UNS K91456 - high expansion steel (AMS 5625) d. UNS S32100 - corrosion and heat resistant steel (AMS 5645) e. UNS S34700 - corrosion and heat resistant steel (AMS 5646)
2017-07-17
WIP Standard
AS7474D
This specification covers bolts and screws made from a corrosion and heat resistant, martensitic iron base alloy of the type identified under the Unified Numbering System as UNS S17400. The following specification designations and their properties are covered: AS7474 140 ksi minimum ultimate tensile strength at room temperature 100 ksi stress corrosion test 72 ksi to 7.2 ksi tension-tension fatigue; AS7474-1 140 ksi minimum ultimate tensile strength at room temperature 100 ksi stress corrosion test 88 ksi minimum ultimate shear strength at room temperature.

Primarily for aerospace propulsion system applications where corrosion resistance and high strength in tension is required in temperatures not to exceed 600 °F.

2017-06-26
WIP Standard
ARP6481
This SAE Aerospace Recommended Practice (ARP) describes a method for assessing size dependent particle losses in a sampling and measurement system of specified geometry utilizing on the non-volatile PM (nvPM) mass and number concentrations measured at the end of the sampling system. The penetration functions of the sampling and measurement system may be determined either by measurement or by analytic computational methods. Loss mechanisms including thermophoretic (which has a very weak size dependence) and size dependent losses are considered in this method along with the uncertainties due to both measurement error and the assumptions of the method. The results of this system loss assessment allow development of estimated correction factors for nvPM mass and number concentrations to account for the system losses facilitating estimation of the nvPM mass and number at the engine exhaust nozzle exit plane.
2017-06-21
WIP Standard
AIR1419C
This document addresses many of the significant issues associated with effects of inlet total-pressure distortion on turbine-engine performance and stability. It provides a review of the development of techniques used to assess engine stability margins in the presence of inlet total-pressure distortion. Specific performance and stability issues that are covered by this document include total-pressure recovery and turbulence effects and steady and dynamic inlet total-pressure distortion.
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