Probabilistic Rotor Design System (PRDS) -- Gas Turbine Engine Design

1998 ◽  
Author(s):  
P. G. Roth
Keyword(s):  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Design System ◽  
Turbine Engine ◽  
Rotor Design ◽  
Engine Design

Gas Turbine Engine: Design, Application and Performance Analysis

2019 ◽  
pp. 115-126
Author(s):  
Abdulkarim Nasir ◽  
Abubakar Mohammed ◽  
Jonathan Y. Jiya
Keyword(s):  
Performance Analysis ◽  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Turbine Engine ◽  
Engine Design ◽  
And Performance

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

2011 ◽  
Author(s):  
August J. Rolling ◽  
Aaron R. Byerley ◽  
Charles F. Wisniewski
Keyword(s):  
Engineering Design ◽  
Gas Turbine ◽  
Systems Engineering ◽  
Aircraft Engine ◽  
Gas Turbine Engine ◽  
Turbine Engine ◽  
Technical Management ◽  
Engine Design ◽  
Aeronautical Engineering ◽  
The Many

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.

Review of Titanium Application in Gas Turbine Engines

2003 ◽  
Author(s):  
Charles W. Elrod
Keyword(s):  
Gas Turbine ◽  
Selection Process ◽  
Gas Turbine Engine ◽  
Advanced Materials ◽  
Turbine Engines ◽  
Turbine Engine ◽  
Long Run ◽  
Engine Design ◽  
Basic Studies ◽  
Burn Rate

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.

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

2011 ◽  
Vol 134 (2) ◽  
Author(s):  
August J. Rolling ◽  
Aaron R. Byerley ◽  
Charles F. Wisniewski
Keyword(s):  
Engineering Design ◽  
Gas Turbine ◽  
Air Force ◽  
Systems Engineering ◽  
Aircraft Engine ◽  
The United States ◽  
Gas Turbine Engine ◽  
Turbine Engine ◽  
Engine Design ◽  
Aeronautical Engineering

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.

By Leaps and Bounds: The Realization of Jet Propulsion through Innovative Materials and Design

2008 ◽  
Vol 380 ◽  
pp. 135-146
Author(s):  
Gene A. Danko
Keyword(s):  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Turbine Engine ◽  
Jet Propulsion ◽  
Engine Design ◽  
Product Generation ◽  
Innovative Materials

Innovations in gas turbine engine design and materials are tracked from the earliest days of functional engines to the present. Materials and design are shown to be mutually interdependent, driving engine capability to unprecedented levels of performance with each succeeding product generation.

Innovative Gas Turbine Engine Cycle Aerothermodynamical Analysis

2013 ◽  
Author(s):  
Mustafa M. Ezzuldeen
Keyword(s):  
Gas Turbine ◽  
Feasibility Studies ◽  
Gas Turbine Engine ◽  
Inlet Temperature ◽  
Turbine Inlet Temperature ◽  
Flow Paths ◽  
Turbine Engine ◽  
Engine Design ◽  
Serial Connection ◽  
Module Size

The gas turbine engine design is fundamentally, taking the air flow into the compressing stage then combustion stage to add energy, and finally extracting energy in the turbine module. This journey of the flow in the engine is in serial connections. Posing the problem of the limiting turbine inlet temperature, the number that all the turbomachinery engineers desperately want to increase by tuning the inlet stages materials, or fine changes onto the blades’ profile or the flow paths. But the significant increase to this temperature lies under more fundamental and radical redesigns to the theory of the gas turbine operation, and its thermodynamical cycle. These principles were considered for long untouchable facts, and stayed lurking from the engineers examining eyes. This paper introduces one of these possibilities by genuine redesign concepts. Backed with CFD analysis, and Thermodynamical feasibility studies to address the potential problems of these modifications. The redesigns include implementing the new concept of the contra-rotating turbine more effectively to reduce the turbine module size, connecting pressurized fluid streams of two counter-rotating compressors in parallel instead of the serial connection, forming a protecting Pressurized shield for the entry turbine stages and, Extracting the energy in the process flow using flows interactions instead of flow-blades interactions.

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