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A variation of a jet engine known as a turboshaft engine is designed to provide shaft power rather than thrust, which is used to power machinery.
Helicopters and auxiliary power units are two applications that frequently use turboshaft engines because they require a tiny, powerful, light engine.
With the exception of the hot gases being expanded to a lower pressure in the turbine, which results in little exhaust velocity, turboprop engines are equivalent to turboprop engines.
The Global aircraft turboshaft engine market accounted for $XX Billion in 2023 and is anticipated to reach $XX Billion by 2030, registering a CAGR of XX% from 2024 to 2030.
RECENT PRODUCT DEVELOPMENT OF AIRCRAFT TURBOSHAFT ENGINE MARKET
The United Engine Corporation of Russia is extending its range of turboshaft engines for rotorcraft. The Klimov VK-2500 and Klimov TV7-117V engines are now two of the export-focused products in the company’s lineup.
Developed by Pratt & Whitney Canada, Inc., the PW200 series engines are compact free-turbine turboshaft engines. Twin-engine helicopters use this engine, which has a horsepower range of 450 to 650. By continuously monitoring engine conditions, it avoids hot starts, compressor stalls, overspeed, etc.
The most recent and technologically sophisticated member of Honeywell’s family of military engines, which also includes the illustrious T55 engine that has propelled the H-47 fleet, is the HTS7500 turboshaft engine.
The HTS7500 is an extremely dependable engine made to function well in harsh conditions and to protect military troops.
MARKET DYNAMICS AIRCRAFT TURBOSHAFT ENGINE MARKET
Due to the highly coupled nature of the many rotorcraft design disciplines, the development of modern rotorcraft aircraft has a number of unique issues; as a result, the usage of an integrated product and process development (IPPD) methodology is required to drive the design solution.
The great bulk of the current propulsion system design resources are concentrated on fixed-wing applications with very little reference to the utilisation of turboshaft engines.This technique accomplishes the design synthesis of multiple product and process needs through the use of simultaneous design and analysis, which is crucial for eventually satisfying the customer’s requests.
By using the annual American Helicopter Society (AHS) Student Design Competition as the design requirement catalyst, Georgia Tech’s Center for Excellence in Rotorcraft Technology (CERT) has continuously focused on improving this IPPD approach within its rotorcraft design course.
Despite this wealth of knowledge, the documentation of this basic rotorcraft design approach is now outdated or falls short of addressing a contemporary IPPD methodology. This need for updated documentation is more frequent in the design of propulsion systems than in any other design discipline, particularly in the field of gas turbine technology.
Furthermore, the majority of rotorcraft design resources focus primarily on aerodynamic factors while generally ignoring the integration of propulsion systems. The goal of this project is to close this knowledge gap by creating a preliminary turboshaft engine design technique that may be used to solve a variety of prospective rotorcraft propulsion system design issues.
Beginning with a review of the basic performance and mission requirements specified in a specific request for proposals, the preliminary engine design process first defines the design space.The choice of the engine cycle is then made, and in-depth parametric and engine performance analysis is performed using programs like GasTurb and the NASA Engine Performance Program (NEPP).
To aid in configuration trade studies and to produce more thorough engine performance and geometry data, fundamental engine component design issues are underlined. The Georgia Tech Generic Helicopter, a two-place, turbine training helicopter, is used as the basis for a thorough engine design case study that is incorporated throughout this methodology (GTGH).
This illustration highlights the degree of integration and detail necessary for each stage of the preliminary turboshaft engine design technique and serves as a constant reference for propulsion system design.
