Integrating Systems Engineering Into the USAF Academy Capstone Gas Turbine Engine Course

Author(s):  
August J. Rolling ◽  
Aaron R. Byerley ◽  
Charles F. Wisniewski

This paper is intended to serve as a template for incorporating technical management majors into a traditional engineering design course. In 2002, the Secretary of the Air Force encouraged the USAF Academy to initiate a new interdisciplinary academic major related to systems engineering. This direction was given in an effort to help meet the Air Force’s growing need for “systems” minded officers to manage the development and acquisition of its ever more complex weapons systems. The curriculum for the new systems engineering management (SEM) major is related to the “engineering of large, complex systems and the integration of the many subsystems that comprise the larger system” and differs in the level of technical content from the traditional engineering major. The program allows emphasis in specific cadet-selected engineering tracks with additional course work in human systems, operations research, and program management. Specifically, this paper documents how individual SEM majors have been integrated into aeronautical engineering design teams within a senior level capstone course to complete the preliminary design of a gas turbine engine. As the Aeronautical engineering (AE) cadets performed the detailed engine design, the SEM cadets were responsible for tracking performance, cost, schedule, and technical risk. Internal and external student assessments indicate that this integration has been successful at exposing both the AE majors and the SEM majors to the benefits of “systems thinking” by giving all the opportunity to employ SE tools in the context of a realistic aircraft engine design project.

Author(s):  
August J. Rolling ◽  
Aaron R. Byerley ◽  
Charles F. Wisniewski

This paper is intended to serve as a template for incorporating technical management majors into a traditional engineering design course. In 2002, the Secretary of the Air Force encouraged the United States Air Force (USAF) Academy to initiate a new interdisciplinary academic major related to systems engineering. This direction was given in an effort to help meet the Air Force’s growing need for “systems” minded officers to manage the development and acquisition of its ever more complex weapons systems. The curriculum for the new systems engineering management (SEM) major is related to the “engineering of large, complex systems and the integration of the many subsystems that comprise the larger system” and differs in the level of technical content from the traditional engineering major. The program allows emphasis in specific cadet—selected engineering tracks with additional course work in human systems, operations research, and program management. Specifically, this paper documents how individual SEM majors have been integrated into aeronautical engineering design teams within a senior level capstone course to complete the preliminary design of a gas turbine engine. As the Aeronautical Engineering (AE) cadets performed the detailed engine design, the SEM cadets were responsible for tracking performance, cost, schedule, and technical risk. Internal and external student assessments indicate that this integration has been successful at exposing both the AE majors and the SEM majors to the benefits of “systems thinking” by giving all the opportunity to employ SE tools in the context of a realistic aircraft engine design project.


Author(s):  
А. Михайлов ◽  
A. Mikhaylov ◽  
В. Михайлов ◽  
V. Mikhailov ◽  
Д. Михайлов ◽  
...  

In the paper presented there is carried out an analysis of peculiarities in the operation of structural elements and subsystems of gas turbine engine (GTE). A GTE structural reliability is investigated which is defined at the stage of aircraft engine design. There are shown structural logistic formulae of aircraft engine reliability. In the work there is offered a general approach to the life increase of GTE structural elements on the basis of functionally-directed properties. Basic principles for the support of functionally-directed properties of the GTE element base are shown. The ways to ensure a specified rated or limit GTE life on the basis of functionally-directed properties of elements are shown.


Author(s):  
Charles W. Elrod

With the continuing desire to make engines with a high thrust to weight advantage, titanium is the metal of choice for the gas turbine engine. The use of titanium in the engine must be considered with reasonable care. The metal has been known to combust under certain conditions. The Air Force conducted a number of studies to evaluate the use of titanium in the engine and in other environments. As a result of the studies the effects the environment, the alloying, the thickness and burn rate were among the conditions evaluated. Also the studies were conducted to determine the self-sustained combustibility of titanium and its alloys in the various situations that were established for the evaluations. The studies considered fifty-four different titanium alloys, which included a sample of most of the current materials, some of the advanced materials and a number of unusual alloys. This effort resulted in the identification of easy to burn, harder to burn and very difficult to burn alloys. With this information we can now look at issues related to where certain alloys would benefit the compressor the most. For example, Ti 6Al4V would most likely be used in the fan section of the compressor, due to the thickness of the blade, the low pressure in that section and the gap above the blade. The compressor has a number of issues that can be partially resolved with the use of titanium in a manner that is consistent with safe procedures. This report will examine these issues and present some considerations that should be considered when applying titanium to the gas turbine engine. This paper will look into the turbine engine and examine those areas where the potential for compressor fires are likely and make suggestions on ways to limit the potential for catastrophic damage and in the long run make the engine more resilient in the future. This paper will examine the problems that have followed the engine development with titanium as one of the major players in the selection process. We will describe some of the technology which makes the use of titanium safer. Titanium will be with the engine technology for some time and the goal of most design and research studies should be to make that time as safe and reliable as possible. This paper will show how research can provide the valuable link from basic studies to engine design.


Author(s):  
A. Yu. Tkachenko ◽  
I. N. Krupenich

Computer-aided system of gas turbine engine calculation and analysis (ASTRA) developed at the Aircraft Engine Theory department of Samara State Aerospace University is described. Its functional capabilities and development of gas turbine engine simulators for various initial-stage design tasks are described.


Author(s):  
B. Arul Jothi ◽  
A. M. Junaid Basha

The Integrated Nozzle Actuating System (INAS) of a gas turbine engine is used to vary the exhaust nozzle area to achieve an optimum performance. The nozzle actuating system is operated by four actuators driven by an Integrated Hydraulic Power Pack (IHPP) connected to the Engine Gear Box (EGB). The quality of the oil operating the precision hydraulic actuators of the INAS should be maintained contamination free to achieve an optimum efficiency of the actuators. Hence a fine hydraulic filter is used in the IHPP circuit to maintain the cleanliness level of the hydraulic oil operating the actuators. The design and development of a hydraulic filter for an aircraft engine is a challenging task involving material selection, manufacturing process quality control and stringent performance qualification test schedule to follow the International standards. The present work describes the development of a 10 micron hydraulic filter operating at 30 bar pressure with a flow of 20 lpm designed according to the specifications of a typical aircraft gas turbine engine IHPP system. The filter has been qualified through all the tests prescribed by the International MIL-F-8815E standards. The tests like Multi-pass test, cold start test, Flow fatigue test, extreme temperature test, vibration test and bubble point test are described and the results are discussed.


Sign in / Sign up

Export Citation Format

Share Document