This document provides an overview of materials used in gas turbine components such as compressors, combustors, turbines, and nozzles. It discusses the challenges associated with each component and how material requirements have evolved over time. For compressors, titanium alloys are widely used due to their high strength to weight ratio, with Ti-6Al-4V being common. Superalloys are needed for the last compressor stages due to higher temperatures. Combustor materials require high temperature creep resistance and oxidation resistance, leading to the use of nickel and cobalt-based superalloys. Turbine disks were initially made of steel but now use nickel-based superalloys like alloy 718 for their high strength. Blades and van

1. MOTILAL NAHRU NATIONAL INSTITUTE
OF TECHNOLOGY
APPLIED MECHANICS DEPARTMENT
(2015-2017)
MATERIALS FOR GAS TURBINE - AN
OVERVIEW
Submitted by: Abhishek Shrivastava

2. APPROACH FOR MATERIAL
SELECTION
 Initial Approach
Ability to withstand at elevated temperature.
 Strength to weight ratio play vital role in weight reduction.
 Change in approach with elevation in operating temperature, leads
to consideration towards:
 Stress Rapture life and Creep properties.
 Low cycle fatigue life.
 Oxidation and hot corrosion resistant.

3. COMPRESSOR IN GAS TURBINE
 Challenges:- High Strength, Centrifugal stress, Fatigue,
Temperature range upto 1200˚F
Titanium Alloy, due to its high strength to weight ratio.
 Titanium content has increased from 3 % in 1950s to about 33% today of the aero engine weight.
 Ti-6Al-4V is used for static and rotating components in gas turbine engines.
 Ti-8Al-1Mo-1V is used for fan blades in military engines (Bayer, 1996).
 The alloys 685 (Ti-6Al-5Zr-0.5Mo-0.25Si) and 829 (Ti-5.5Al-3.5Sn-3Zr-1Nb-0.25Mo-0.3Si) are used in
many current European aero engines.
 Alloy 834 (Ti-5.8Al-4Sn-3.5Zr-0.7Nb-0.5Mo-0.35Si-0.06C) used as a compressor disc material in the
last two stages of the medium-pressure compressor, and the first four stages of the high pressure
compressor in variants of the Rolls-Royce Trent series commercial jet engine.
Ti-1100 (Ti-6Al-2.8Sn-4Zr-0.4Mo-0.4Si used in the heat treated condition. The alloy has a claimed use
temperature of 600 oC.
 Ti6-2-4-2S contains additional 0.1-0.25 % Si to improve the creep resistance. It is used for rotating
components such as blades, discs and rotors at temperatures up to about 540 oC (Bayer, 1996).

4. LIMITATION FOR MATERIALS OF
COMPRESSOR The discs and blades of the last compressor stages, have to be
manufactured from Ni-based super alloys at nearly twice the weight.
 Different thermal expansion behaviour and the bonding techniques
of the two alloy systems.
 The temperature limitation for titanium alloys upto 600˚C.

5. COMPRESSOR BLADE MATERIALS
FOR LAND BASED GAS TURBINES
 Blades for compressors are made from 12% chromium containing
martensitic stainless steel grades 403 or 403 Cb (Schilke, 2004).
 To prevent the corrosion, GE has developed patented aluminum
slurry coatings for the compressor blades, it also impart erosion
resistant.
 During the 1980’s, GE introduced a new compressor blade material,
GTD-450, which without sacrificing stress corrosion resistance,
increased tensile strength, high cycle fatigue strength and corrosion
fatigue strength, It also possesses superior resistance to acidic salt
environments.

6. COMBUSTOR
 Challenges:-
 Improvement of high temperature creep rupture strength without sacrificing the
oxidation / corrosion resistance.
 Nickel-base superalloys. Hastelloy X, a material with higher creep
strength was used from 1960s to 1980s.
 Nimonic 263 has still higher creep strength (Schilke, 2004).
 HA-188, a cobalt base superalloy, for improved creep rupture
strength, 1987.
 Nickel base superalloys 617 and 230 find wide application for
combustor components (Wright & Gibbons, 2007).
 Combustion liners and transition pieces are given a thermal barrier
coating (TBC), which provides an insulating layer and reduces the
underlying base metal temperature.

7. TURBINE DISK
 A286, an austenitic iron-base alloy and Superalloy 718 has been
used for manufacture of discs in aircraft engines for many years.
PM technique leads to easy production of Nickle based superalloys,
which provides higher strength than conventional techniques.
 Improved homogeneity and uniformity.
 In 1965, 1%Cr-1.25%Mo-0.25%V steel in hardened and tempered
condition were used. 12%Cr steels have higher rupture strength than
Cr-Mo-V steel, fracture toughness and capacity.
 With higher firing temperatures use of nickel-base superalloy, alloy
706 for the rotors. Alloy 718, the most frequently used superalloy for
aircraft gas turbines.

8. TURBINE BLADES AND VANES
 Challenges:- High Temp., creep and oxidation resistant.
 Wrought alloys with increase level of aluminium based alloy.
Problem Forgeability.
 Cast nickel-base alloys: 1) Good high temp strength
2)Coarse grain size of casting.
Buckets & Nozzle:- Sever combination of temperature, stress and
environment.
 Rene 41, Rene 77, Rene 100, IN100 having relatively high chromium
content for improved corrosion resistance at the cost of some high
temperature strength.

9. NOZZLE MATERIALS
 FSX 414, a GE-patented cobalt base alloy for all stage nozzles. Cobalt base
alloys possess superior strength at very high temperatures.
 Enables increased firing temperatures for a given oxidation life (Schilke, 2004).
Nickel base superalloy, GTD222 for some stage 2 and stage 3 applications. The
alloy has significantly higher creep strength.
 To avoid Nucleation and growth of cavities along transverse grain boundaries
DS superalloys were used. It improved the turbine blade metal temperature
capability by about 14 oC relative to the conventionally cast superalloys.

10. VANES
 Oxide Dispersion Strengthened (ODS) superalloys.
-retain useful strength up to a relatively high fraction of their
melting point.
-MA754 has been in production by General Electric as a vane material
since 1980. Because of its high long time elevated temperature strength, it
has been extensively used for aircraft gas turbine.

11. COATING ON TURBINE BLADE
The functions of coating are:-
 It acts as reservoir of elements which will form very protective and
adherent oxide layers.
 Protecting the underlying base material from oxidation, corrosion attack
and degradation.
Types of Coating:-
Aluminide (diffusion) coatings
Overlay coatings
Thermal barrier coatings (TBCs)

12. ADVANCED MATERIALS UNDER R&D
Ceramics
 Turbines would then operate at higher temperatures, yielding
higher power with smaller engine sizes.
 Ceramics are also up to 40% lighter than comparable high
temperature alloys.
They also cost much less – their cost is around 5% the cost of
superalloys.
 Problem of brittleness.
Intermetallics
 Because of low density it helps in redusing weight of engine.
Problem:- fracture toughness and resistance to growth of fatigue

13. Composites
• Polymer matrix composites
- in the cold section of jet engines, resulting in substantial weight savings.
Titanium based metal matrix composites
- weight reduction of about 70%.
- Limitation: fibre-matrix interaction leading to the degradation of
properties.
Ceramic matrix composites (CMCs)
- achievement of increasing operating temperatures without incurring the
penalties associated with increased cooling air used.
- They are tough, although their constituents are intrinsically brittle.
- Replacing the superalloys by light, tough, refractory and creep resistant SiC -
matrix composites.

14. REFERENCES
 http://www.intechopen.com/books/advances-in-gas-turbine-
technology/materials-for-gas-turbines-an-overview
 Alven, D.A. Refractory- and Precious Metal- Based Superalloys, JOM,
Vol.56, No.9, pp 27 ISSN 1047-4838.
Advances in Gas Turbine Technology
Edited by Dr. Ernesto Benini
ISBN 978-953-307-611-9
Hard cover, 526 pages
Publisher InTech
Published online 04, November, 2011
Published in print edition November, 2011
 Nageswara Rao Muktinutalapati (2011). Materials for Gas Turbines – An
Overview, Advances in Gas Turbine Technology, Dr. Ernesto Benini (Ed.),
ISBN: 978-953-307-611-9

15. Thank