Thermodynamic Analysis Of An Aeroderivative Gas Turbine Engine System With Ceramic Matrix Composite Rotating Blades NIT Jamshedpur

Format:

Book

Conference/Event

Author/Creator:

Rathore, Souvik Singh, author.

Contributor:

Kar, Vishesh

Mishra, Shivam

S, Sanjay

Conference Name:

AeroTech Digital Summit (2021-03-09 : Live Online, Pennsylvania, United States)

Language:

English

Physical Description:

1 online resource cm

Place of Publication:

Warrendale, PA SAE International 2021

Summary:

The quest for achieving more efficient gas turbine engine systems (GTESs) has led the researchers to try getting into many new dimensions of research. Simple Brayton Cycle based plants were coupled with recuperators, regenerators and reheaters to avoid heat energy wastage and this formed Complex GTESs. Multistage compression in axial compressors and multistage expansions in turbines paved the path to optimize the plant design for greater thrust to weight ratio and greater efficiency of the GTESs. Since the increase in efficiency of any power plant is directly or indirectly related to temperatures at which the plant cycle is being operated, this thermodynamic constraint had led to the development of high temperature bearing materials such as single crystal Nickel based superalloys. To further aid the increment in operating temperature, different blade cooling techniques were adopted and thermal barrier coatings were applied on blades and thus, the present-day gas turbine blades are able to operate over 1500 C. Today, researchers and scientists are seeking new materials that can bear higher temperatures when compared to conventional Nickel based alloys as blade material. Although ceramics are known to be able to endure extremely high temperatures, owing to their brittleness, they are not formed into blades. On the other hand, ceramic matrix composites (CMCs) are being considered as a new alternative material which have high fracture toughness besides high temperature bearing capacity. A comparative study of the thermodynamic analysis of an aeroderivative gas turbine engine system with CMC blades and conventional Nickel based superalloy blades has been done. It is observed that there is a projected efficiency improvement of 2.5 % at a temperature of 1500 K when CMC is used as a blade material

Notes:

Vendor supplied data

Publisher Number:

2021-01-0033

Access Restriction:

Restricted for use by site license