Experimental Results of a Transpiration-Cooled Turbine Operated in an Engine for 150 Hours at 2500 F Turbine Inlet Temperature

1967 ◽  
Author(s):  
S. Lombardo ◽  
S. L. Moskowitz ◽  
S. A. Schnure
Keyword(s):  
Effective Means ◽  
Turbine Blades ◽  
Strength Properties ◽  
Inlet Temperature ◽  
High Melting Point ◽  
Turbine Inlet Temperature ◽  
Supersonic Aircraft ◽  
Melting Temperatures ◽  
Turbine Inlet ◽  
Long Life

A key element in the development of gas turbine powerplants for advanced subsonic and supersonic aircraft is the ability to operate at turbine inlet temperatures significantly above the 1600–1800 F limit of today. This limit is imposed by the fact that current materials available for use in turbines exhibit inadequate strength and oxidation characteristics above 1600–1800 F. Certain metals such as molybdenum, chromium, tungsten and other high-melting-point alloys show good strength properties at temperatures far above which conventional super alloys are useful in turbines. However, these materials lack either the ductility or oxidation resistance necessary for turbine components. A means of realizing the gains possible by operating turbines at high turbine inlet temperatures is through cooling of the highly stressed turbine components. The necessity of reliable and efficient turbine operation for periods of long life in an environment of gas temperatures above the actual melting temperatures of the materials requires that effective means of cooling the blades be developed. The authors discuss the design of transpiration air cooled turbines as a means of operating engines at gas temperatures of 2500 F and higher, utilizing available turbine materials which are limited to metal temperatures between 1600 and 1800 F. The technique utilized in fabricating transpiration air cooled turbine blades is discussed. The results of operating a full-scale J65 engine, modified to incorporate a single-stage turbine fitted with transpiration air cooled blades, for 150 hr at 2500 F turbine inlet temperature are presented.

Long-Life Base Load Service at 1600 F Turbine Inlet Temperature

1967 ◽  
Vol 89 (1) ◽  
pp. 41-46 ◽  
Author(s):  
N. E. Starkey
Keyword(s):  
Inlet Temperature ◽  
Air Cooling ◽  
Turbine Inlet Temperature ◽  
Fuel Distribution ◽  
Design Considerations ◽  
Turbine Inlet ◽  
Accurate Temperature ◽  
Long Life ◽  
Accurate Temperature Control ◽  
Base Load

Design considerations required for base load long-life service at turbine inlet temperature above 1600 F are discussed. These include control of combustion profile, air cooling of the first-stage nozzle, long-shank turbine buckets, accurate air and fuel distribution, and accurate temperature control.

Development of the Advanced Closed-Cycle Gas Turbine System

2001 ◽  
Author(s):  
Miki Koyama ◽  
Toshio Mimaki
Keyword(s):  
Film Cooling ◽  
Cooling System ◽  
Early Stage ◽  
Turbine Blades ◽  
Thermal Conditions ◽  
Inlet Temperature ◽  
Internal Cooling ◽  
Turbine Inlet Temperature ◽  
Turbine Blade Cooling ◽  
Turbine Inlet

This aims to put the fruits of the R&D; “The Hydrogen Combustion Turbine” in WE-NET Phase I Program(1993-1998) to practical use at an early stage. The topping regenerating cycle was selected as the optimum cycle, with energy efficiency expected to be more than 60%(HHV) under the conditions of the turbine inlet temperature of 1973K(1700°C) and the pressure of 4.8MPa,in it. • As the turbine inlet temperature and pressure increase, issues to be resolved include the amount of NOx emissions and the durability of super alloys for turbine blades under such thermal conditions. In this respect, the development of the highly efficient methane-oxygen combustion technology, the turbine blade cooling technology, and the ultrahigh-temperature materials including thermal barrier coatings is being carried out. • In 1999, the results made it clear that there are little error among the three analytic programs used to verify the system efficiency, it was verified that the burning rate was going to arrive at over 98% from the methane-oxygen combustion test (under the atmospheric pressure). And the type of vane “Film cooling plus recycle type with internal cooling system” was selected as the most suitable vane.

A Selective Assembly Method to Reduce the Impact of Blade Flow Variability on Turbine Life

2004 ◽  
Author(s):  
Vince Sidwell ◽  
David Darmofal
Keyword(s):  
Turbine Blades ◽  
High Flow ◽  
Metal Temperature ◽  
Low Flow ◽  
Inlet Temperature ◽  
Selective Assembly ◽  
Turbine Inlet Temperature ◽  
Assembly Method ◽  
Turbine Inlet ◽  
The Impact

A selective assembly method is proposed that decreases the impact of blade passage manufacturing variability on the life of a row of cooled turbine blades. The method classifies turbine blades into groups based on the effective flow areas of the blade passages, then a row of blades is assembled exclusively from blades of a single group. A simplified classification is considered in which blades are divided into low-flow, nominal-flow, and high-flow groups. For rows assembled from the low-flow class, the blade plenum pressure will tend to rise and the individual blade flows will be closer to the design intent than for a single low-flow blade in a randomly-assembled row. Since the blade metal temperature is strongly dependent on the blade flow, selective assembly can lower the metal temperature of the lowest-flowing blades and increase the life of a turbine row beyond what is possible from a randomly-assembled row. Furthermore, the life of a nominal-flow or high-flow row will be significantly increased (relative to a randomly-assembled row) since the life-limiting low-flow blades would not be included in these higher-flowing rows. The impact of selective assembly is estimated using a model of the first turbine rotor of an existing high-bypass turbofan. The oxidation lives of the nominal-flow and high-flow blade rows are estimated to increase approximately 50% and 100% compared to randomly-assembled rows, while the life of the low-flow rows are the same as the randomly-assembled rows. Alternatively, selective assembly can be used to increase turbine inlet temperature while maintaining the maximum blade metal temperatures at random-assembly levels. For the nominal-flow and high-flow classes, turbine inlet temperature increases are estimated to be equivalent to the turbine inlet temperature increases observed over several years of gas turbine technology development.

Comparative Thermodynamic Analysis of Gas Turbine Systems with Turbine Blade Film Cooling

2012 ◽  
Vol 505 ◽  
pp. 539-543
Author(s):  
Kyoung Hoon Kim ◽  
Kyoung Jin Kim ◽  
Chul Ho Han
Keyword(s):  
Gas Turbine ◽  
Turbine Blade ◽  
Thermodynamic Analysis ◽  
Film Cooling ◽  
Pressure Ratio ◽  
Turbine Blades ◽  
Inlet Temperature ◽  
Turbine Inlet Temperature ◽  
Blade Cooling ◽  
Turbine Inlet

Since the gas turbine systems require active cooling to maintain high operating temperature while avoiding a reduction in the system operating life, turbine blade cooling is very important and essential but it may cause the performance losses in gas turbine. This paper deals with the comparative thermodynamic analysis of gas turbine system with and without regeneration by using the recently developed blade-cooling model when the turbine blades are cooled by the method of film cooling. Special attention is paid to investigating the effects of system parameters such as pressure ratio and turbine inlet temperature on the thermodynamic performance of the systems. In both systems the thermal efficiency increases with turbine inlet temperature, but its effect is less sensitive in simpler system

Analysis of Integrated Cooling Systems for Gas Turbine Power Plants

2017 ◽  
Author(s):  
Waleed El-Damaty ◽  
Mohamed Gadalla
Keyword(s):  
Gas Turbine ◽  
Power Plants ◽  
Turbine Blades ◽  
Operating Conditions ◽  
Inlet Temperature ◽  
Air Cooling ◽  
Turbine Inlet Temperature ◽  
Current Increase ◽  
Turbine Inlet ◽  
Compact Size

With the current increase in electricity consumption and energy demand, most of the research focus is shifted towards the means of increasing the power plants efficiency in order to produce more electricity by using as less fuel as possible. Gas turbine power plants specifically have been under the study in the recent years due to its feasibility, low capital cost, simple design, compact size and higher efficiency compared to steam turbine power plants. There are a lot of operating conditions that affect the performance of the gas turbine which includes the inlet air climatic conditions, mass flow rate and the turbine inlet temperature. Many improvements and enhancements became applicable through the advancement in the material and cooling technologies. Cooling techniques could be used to cool the inlet air entering the compressor by utilizing evaporative coolers and mechanical chillers, and to cool the turbine blades in order to avoid a decline in the life of turbine blades due to unwanted exposure to thermal stresses and oxidation. Internal convection cooling, film cooling and transpiration cooling are the three main techniques that can be used in the process of turbine blades cooling. The main objective of this proposal is to improve the durability and performance of gas turbine power plants by proposing the usage of integrated system of solid desiccant with Maisotsenko cooler in the turbine blade cooling and inlet air cooling processes. Four configurations were presented and the results were an increase in the efficiency of the gas turbine cycle for all the cases specially the two stage Maisotsenko desiccant cooling system where the efficiency increased from 33.33% to 34.17% as well as maintaining the turbine inlet temperature at a desired level of 1500°K.

scholarly journals Comprehensive Review on Leading Edge Turbine Blade Cooling Technologies

2021 ◽  
Vol 39 (2) ◽  
pp. 403-416
Author(s):  
Chirag Sharma ◽  
Siddhant Kumar ◽  
Aanya Singh ◽  
Kartik R. Bhat Hire ◽  
Vedant Karnatak ◽  
...  
Keyword(s):  
Turbine Blade ◽  
Turbine Blades ◽  
Leading Edge ◽  
Inlet Temperature ◽  
Turbine Inlet Temperature ◽  
Entire Surface ◽  
Turbine Blade Cooling ◽  
Blade Cooling ◽  
Advantages And Disadvantages ◽  
Turbine Inlet

Developments in the gas turbine technology have caused widespread usage of the Turbomachines for power generation. With increase in the power demand and a drop in the availability of fuel, usage of turbines with higher efficiencies has become imperative. This is only possible with an increase in the turbine inlet temperature (TIT) of the gas. However, the higher limit of TIT is governed by the metallurgical boundary conditions set by the material used to manufacture the turbine blades. Hence, turbine blade cooling helps in drastically controlling the blade temperature of the turbine and allows a higher turbine inlet temperature. The blade could be cooled from the leading edge, from the entire surface of the blade or from the trailing edge. The various methods of blade cooling from leading edge and its comparative study were reviewed and summarized along with their advantages and disadvantages.

2750 Deg F Engine Test of a Transpiration Air-Cooled Turbine

1971 ◽  
Vol 93 (2) ◽  
pp. 238-248 ◽  
Author(s):  
S. L. Moskowitz ◽  
S. Lombardo
Keyword(s):  
Gas Turbine ◽  
High Performance ◽  
Effective Means ◽  
Inlet Temperature ◽  
Test Results ◽  
Gas Temperature ◽  
Supersonic Aircraft ◽  
Turbine Inlet ◽  
Marine Applications ◽  
Turbine Blading

The development of gas turbine engines for advanced subsonic and supersonic aircraft as well as for potential utilization of these high performance engines for stationary and marine applications requires, as a key element, the ability to operate at turbine inlet temperatures above the actual melting temperatures of the turbine materials. A limit on gas temperature levels is imposed by the fact that current alloys available for use in turbines, exhibit inadequate strength and oxidation characteristics above 1600–1800 deg F. However, the performance gains offered by operating engines at a high turbine inlet temperature may be realized through the application of an efficient method of cooling the highly stressed turbine components. As a step toward demonstrating that transpiration cooling of turbine blading is an effective means for achieving reliable and efficient gas turbine operation in a high gas temperature environment, a full-scale engine was tested at average gas temperatures of 2750–2800 deg F with a transpiration cooled turbine fabricated from normally used turbine alloys which are limited to metal temperatures of 1600–1800 deg F. The authors discuss the design of the transpiration air-cooled turbine, the technique used in fabricating the porous turbine blading, and the experimental test results obtained from operating the high-temperature engine. Furthermore, correlation of the test results on blade cooling with analytical predictions is presented.

Approximate Relations for Optimum Turbine Operating Parameters in Allam Cycle

2020 ◽  
Author(s):  
Yousef Haseli
Keyword(s):  
Turbine Blades ◽  
Air Separation ◽  
Cycle Performance ◽  
Working Fluid ◽  
Operating Parameters ◽  
Inlet Temperature ◽  
Turbine Inlet Temperature ◽  
Power Cycle ◽  
Turbine Inlet ◽  
Cycle Efficiency

Abstract The Allam power cycle is a novel method for clean power generation which employs the concept of oxyfuel combustion with carbon dioxide as the main working fluid. To date, only a few studies have appeared in the literature in that the performance of the Allam cycle has been assessed using a commercial software. The objective of this article is to explore relations between the cycle performance and the main operating parameters of the Allam cycle through a simplified thermodynamic analysis and mathematical modeling. The cycle efficiency is maximized with respect to turbine parameters. Expressions are derived for estimation of optimum turbine inlet temperature and pressure as well as optimum turbine exhaust pressure. Main simplifications include no portion of the recycled CO2 is used for turbine blades cooling and single stage CO2 compressor without intercooling. The cryogenic air separation process developed by Allam is employed which produces supercritical oxygen at combustion pressure. Typical numerical results are presented using the new expressions for optimum turbine parameters. The highest cycle efficiency is found to be 66.4% at a turbine inlet temperature/inlet pressure/exhaust pressure of 1306 K/300 bar/39.4 bar and a CO2 compressor exit pressure of 60 bar. The newly derived relationships among the key process parameters allow a better understanding of the operation of Allam cycle.

Status of the Development of the CGT301, a 300 KW Class Ceramic Gas Turbine

1996 ◽  
Author(s):  
Takao Mikami ◽  
Shinya Tanaka ◽  
Masashi Tatsuzawa ◽  
Takeshi Sakida
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Turbine Blades ◽  
Axial Flow ◽  
Inlet Temperature ◽  
Turbine Inlet Temperature ◽  
Turbine Inlet ◽  
All Ceramic ◽  
Ceramic Components ◽  
Primary Type

The CGT301 ceramic gas turbine is being developed under a contract from NEDO as a part of the New Sunshine Program of MTTI to improve the performance of gas turbines for cogeneration through the replacement of hot section components with ceramic parts. The project is conducted in three phases. The project currently in Phase 2 focuses on the development of the “primary type” ceramic gas turbine (turbine inlet temperature: 1,200°C). CGT301 is a recuperated, single-shaft, ceramic gas turbine. The turbine is a two-stage axial flow type. The major effort has been on the development of the turbine which consists of metallic disks and inserted ceramic blades (“hybrid rotor”). Prior to engine tests, component tests were performed on the hybrid rotor to prove the validity of the design concepts and their mechanical integrity. The engine equipped with all ceramic components except the second stage turbine blades was tested and evaluated. The engine was operated successfully for a total of 23 hours without failure at the rated engine speed of 56,000 rpm with the turbine inlet temperature of 1,200 °C. Further, the engine equipped with all ceramic components was successfully tested for one hour under the same conditions. Engine testing of the “primary type” ceramic gas turbine is continuing to improve the performance and the reliability of the system for the purpose of moving forward to the development of the “pilot” ceramic gas turbine (turbine inlet temperature: 1,350 °C) as the final target of this project. This paper summarizes the progress in the development of the CGT301 with the emphasis on the test results of the hybrid rotor.

Sign in / Sign up

Export Citation Format

Share Document