Application of Gas Bearings to Closed-System Brayton-Cycle Turbomachinery—Recent Accomplishments and Potential Problem Areas

1966 ◽  
Vol 88 (4) ◽  
pp. 367-376 ◽  
Author(s):  
P. W. Curwen ◽  
H. F. Jones ◽  
H. Schwarz
Keyword(s):  
Gas Turbine ◽  
Inlet Temperature ◽  
Brayton Cycle ◽  
Test Results ◽  
Development Programs ◽  
Closed Loop System ◽  
Turbine Inlet Temperature ◽  
Gas Bearings ◽  
Shaft Power ◽  
Gas Bearing

Several development programs to demonstrate application of gas-lubricated bearings to gas turbine machinery are presently under way. This paper presents design and initial test data for a 24,000 rpm, 1300 F (turbine inlet temperature) gas-bearing Brayton-cycle turbocompressor operating in a closed-loop system. The bearing system design for a two-shaft power plant, consisting of a 50,000 rpm, 1490 F turbocompressor and a 12,000 rpm turboalternator, is also described. Test results to date demonstrate that gas lubrication, per se, of gas turbine machinery is definitely feasible. However, considerable data are still needed to prove the practical utility of gas bearings. A brief discussion of the needed investigations is presented.

scholarly journals Thermodynamic Analysis and Optimization of a Novel Power-Water Cogeneration System for Waste Heat Recovery of Gas Turbine

Entropy ◽  
2021 ◽  
Vol 23 (12) ◽  
pp. 1656
Author(s):  
Shunsen Wang ◽  
Bo Li
Keyword(s):  
Gas Turbine ◽  
Waste Heat ◽  
Exergy Efficiency ◽  
Inlet Temperature ◽  
Brayton Cycle ◽  
Turbine Inlet Temperature ◽  
Split Ratio ◽  
Preheating Temperature ◽  
Cogeneration System ◽  
Dual Stage

A power-water cogeneration system based on a supercritical carbon dioxide Brayton cycle (SCBC) and reverse osmosis (RO) unit is proposed and analyzed in this paper to recover the waste heat of a gas turbine. In order to improve the system performance, the power generated by SCBC is used to drive the RO unit and the waste heat of SCBC is used to preheat the feed seawater of the RO unit. In particular, a dual-stage cooler is employed to elevate the preheating temperature as much as possible. The proposed system is simulated and discussed based on the detailed thermodynamic models. According to the results of parametric analysis, the exergy efficiency of SCBC first increases and then decreases as the turbine inlet temperature and split ratio increase. The performance of the RO unit is improved as the preheating temperature rises. Finally, an optimal exergy efficiency of 52.88% can be achieved according to the single-objective optimization results.

Hybrid Catalytic Combustion for Stationary Gas Turbine: Concept and Small Scale Test Results

1987 ◽  
Author(s):  
Tomiaki Furuya ◽  
Terunobu Hayata ◽  
Susumu Yamanaka ◽  
Junji Koezuka ◽  
Toshiyuki Yoshine ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Gas Phase ◽  
Gas Turbines ◽  
Catalytic Combustion ◽  
Small Scale ◽  
Inlet Temperature ◽  
Test Results ◽  
Turbine Inlet Temperature ◽  
Scale Test ◽  
Near Future

Catalytic combustion for gas turbine applications has been investigated. Its significant advantages in reducing combustor emissions, particularly nitrogen oxides (NOx), have been shown. One of the main problems in regard to developing a catalytic combustor is the durability of catalysts, because the catalysts deteriorate during high temperature operation, which is normal for current gas turbines and near future gas turbines. The hybrid catalytic combustion concept has advantages concerned with catalyst durability. This paper shows its concept and small scale test results. This hybrid catalytic combustion concept comprises the following steps; premix fuel and air for a catalyst-packed zone; operate catalysts at rather low temperatures, to prolong catalyst life; add fresh fuel into the stream at the catalyst-packed zone outlet, where gas phase combustion occurs completely without a catalyst; add dilution air into the stream at the gas phase combustion zone outlet with a by-pass valve. Experimental data and analyses indicated that this hybrid catalytic combustion has a potential of being applicable to current gas turbines (turbine inlet temperature is about 1100°C) and near future gas turbines (turbine inlet temperature is about 1300°C).

Current Status of 300 kW Industrial Gas Turbine R&D in Japan

1995 ◽  
Author(s):  
Takumi Murayama ◽  
Kunihiro Nagata ◽  
Hiroyuki Abe ◽  
Hisao Ogiyama
Keyword(s):  
Energy Efficiency ◽  
International Trade ◽  
Environmental Protection ◽  
Gas Turbine ◽  
Science And Technology ◽  
Current Status ◽  
Inlet Temperature ◽  
Test Results ◽  
Turbine Inlet Temperature ◽  
Industrial Gas Turbine

The Ceramic Gas Turbine (CGT) has great advantages in terms of energy efficiency, environmental protection, and fuel-diversification. In Japan, R&D on the 300 kW CGT has been carried out as one of the national projects entitled “New Sunshine Program”, which are promoted by the New Sunshine Project Promotion Headquarters, Agency of Industrial Science and Technology (AIST), Ministry of International Trade and Industry (MITI). R&D on the CGT has progressed faithfully and now the operation of prototype CGTs (Turbine Inlet Temperature (TIT) of 1200 °C) is focused. In the paper, the overall status of the R&D activities on the 300 kW CGT will be reviewed with the test results to-date, problems awaiting solution, and perspective for the prototype and pilot CGTs.

Development and Fabrication of Silicon Nitride Components for Ceramic Gas Turbine

1997 ◽  
Author(s):  
Keisuke Makino ◽  
Ken-Ichi Mizuno ◽  
Toru Shimamori
Keyword(s):  
High Temperature ◽  
Silicon Nitride ◽  
Gas Turbine ◽  
Gas Turbines ◽  
Turbine Blades ◽  
High Strength ◽  
Inlet Temperature ◽  
Turbine Inlet Temperature ◽  
Spark Plug ◽  
Power Turbine

NGK Spark Plug Co., Ltd. has been developing various silicon nitride materials, and the technology for fabricating components for ceramic gas turbines (CGT) using theses materials. We are supplying silicon nitride material components for the project to develop 300 kW class CGT for co-generation in Japan. EC-152 was developed for components that require high strength at high temperature, such as turbine blades and turbine nozzles. In order to adapt the increasing of the turbine inlet temperature (TIT) up to 1,350 °C in accordance with the project goals, we developed two silicon nitride materials with further unproved properties: ST-1 and ST-2. ST-1 has a higher strength than EC-152 and is suitable for first stage turbine blades and power turbine blades. ST-2 has higher oxidation resistance than EC-152 and is suitable for power turbine nozzles. In this paper, we report on the properties of these materials, and present the results of evaluations of these materials when they are actually used for CGT components such as first stage turbine blades and power turbine nozzles.

Rolls Royce/Allison 501-K Gas Turbine Anti-Fouling Compressor Coatings Evaluation

2002 ◽  
Author(s):  
Daniel E. Caguiat
Keyword(s):  
Gas Turbine ◽  
Fuel Consumption ◽  
Gas Turbines ◽  
Performance Degradation ◽  
Specific Fuel Consumption ◽  
Inlet Temperature ◽  
Test Results ◽  
Turbine Inlet ◽  
Compressor Performance ◽  
Compressor Efficiency

The Naval Surface Warfare Center, Carderock Division (NSWCCD) Gas Turbine Emerging Technologies Code 9334 was tasked by NSWCCD Shipboard Energy Office Code 859 to research and evaluate fouling resistant compressor coatings for Rolls Royce Allison 501-K Series gas turbines. The objective of these tests was to investigate the feasibility of reducing the rate of compressor fouling degradation and associated rate of specific fuel consumption (SFC) increase through the application of anti-fouling coatings. Code 9334 conducted a market investigation and selected coatings that best fit the test objective. The coatings selected were Sermalon for compressor stages 1 and 2 and Sermaflow S4000 for the remaining 12 compressor stages. Both coatings are manufactured by Sermatech International, are intended to substantially decrease blade surface roughness, have inert top layers, and contain an anti-corrosive aluminum-ceramic base coat. Sermalon contains a Polytetrafluoroethylene (PTFE) topcoat, a substance similar to Teflon, for added fouling resistance. Tests were conducted at the Philadelphia Land Based Engineering Site (LBES). Testing was first performed on the existing LBES 501-K17 gas turbine, which had a non-coated compressor. The compressor was then replaced by a coated compressor and the test was repeated. The test plan consisted of injecting a known amount of salt solution into the gas turbine inlet while gathering compressor performance degradation and fuel economy data for 0, 500, 1000, and 1250 KW generator load levels. This method facilitated a direct comparison of compressor degradation trends for the coated and non-coated compressors operating with the same turbine section, thereby reducing the number of variables involved. The collected data for turbine inlet, temperature, compressor efficiency, and fuel consumption were plotted as a percentage of the baseline conditions for each compressor. The results of each plot show a decrease in the rates of compressor degradation and SFC increase for the coated compressor compared to the non-coated compressor. Overall test results show that it is feasible to utilize anti-fouling compressor coatings to reduce the rate of specific fuel consumption increase associated with compressor performance degradation.

Practical Implications of Integrating Turbomachinery Into the Air Turborocket

2004 ◽  
Author(s):  
Joshua A. Clough ◽  
Mark J. Lewis
Keyword(s):  
Gas Turbine ◽  
Aircraft Engine ◽  
Launch Vehicle ◽  
Turbine Engines ◽  
Inlet Temperature ◽  
Gas Turbine Engines ◽  
Turbine Inlet Temperature ◽  
Turbine Engine ◽  
Space Launch ◽  
Practical Implications

The development of new reusable space launch vehicle concepts has lead to the need for more advanced engine cycles. Many two-stage vehicle concepts rely on advanced gas turbine engines that can propel the first stage of the launch vehicle from a runway up to Mach 5 or faster. One prospective engine for these vehicles is the Air Turborocket (ATR). The ATR is an innovative aircraft engine flowpath that is intended to extend the operating range of a conventional gas turbine engine. This is done by moving the turbine out of the core engine flow, alleviating the traditional limit on the turbine inlet temperature. This paper presents the analysis of an ATR engine for a reusable space launch vehicle and some of the practical problems that will be encountered in the development of this engine.

scholarly journals High-Temperature Turbine Technology Readiness

1982 ◽  
Author(s):  
M. W. Horner ◽  
A. Caruvana
Keyword(s):  
High Temperature ◽  
Gas Turbine ◽  
Phase Ii ◽  
Combined Cycle ◽  
Technology Readiness ◽  
Inlet Temperature ◽  
Test Results ◽  
Turbine Inlet ◽  
Combined Cycle Plant ◽  
Gas Fuel

Final component and technology verification tests have been completed for application to a 2600°F rotor inlet temperature gas turbine. These tests have proven the capability of combustor, turbine hot section, and IGCC fuel systems and controls to operate in a combined cycle plant burning a coal-derived gas fuel at elevated gas turbine inlet temperatures (2600–3000°F). This paper presents recent test results and summarizes the overall progress made during the DOE-HTTT Phase II program.

A Parametric Analysis for Optimal Selection of a Gas Turbine Cogeneration System

2004 ◽  
Author(s):  
K. Sarabchi ◽  
A. Ansari
Keyword(s):  
Gas Turbine ◽  
Pressure Ratio ◽  
Computer Code ◽  
Primary Energy ◽  
Inlet Temperature ◽  
Fuel Cost ◽  
Energy Usage ◽  
Turbine Inlet Temperature ◽  
Cogeneration System ◽  
Selection Of

Cogeneration is a simultaneous production of heat and electricity in a single plant using the same primary energy. Usage of a cogeneration system leads to fuel energy saving as well as air pollution reduction. A gas turbine cogeneration plant (GTCP) has found many applications in industries and institutions. Although fuel cost is usually reduced in a cogeneration system but the selection of a system for a given site optimally involves detailed thermodynamic and economical investigations. In this paper the performance of a GTCP was investigated and an approach was developed to determine the optimum size of the plant to meet the electricity and heat demands of a given site. A computer code, based on this approach, was developed and it can also be used to examine the effect of key parameters like pressure ratio, turbine inlet temperature, utilization period, and fuel cost on the economics of GTCP.

scholarly journals Development of 300 kW Class Ceramic Gas Turbine (CGT302)

1995 ◽  
Author(s):  
Kozi Nishio ◽  
Junzo Fujioka ◽  
Tetsuo Tatsumi ◽  
Isashi Takehara
Keyword(s):  
Gas Turbine ◽  
Development Program ◽  
Pollutant Emissions ◽  
Turbine Engines ◽  
Inlet Temperature ◽  
Gas Turbine Engines ◽  
Turbine Inlet Temperature ◽  
Iso Standard ◽  
Current State ◽  
Ceramic Components

With the aim of achieving higher efficiency, lower pollutant emissions, and multi-fuel capability for small to medium-sized gas turbine engines for use in co-generation systems, a ceramic gas turbine (CGT) research and development program is being promoted by the Japanese Ministry of International Trade and Industry (MITI) as a part of its “New Sunshine Project”. Kawasaki Heavy Industries (KHI) is participating in this program and developing a regenerative two-shaft CGT (CGT302). In 1993, KHI conducted the first test run of an engine with full ceramic components. At present, the CGT302 achieves 28.8% thermal efficiency at a turbine inlet temperature (TIT) of 1117°C under ISO standard conditions and an actual TIT of 1250°C has been confirmed at the rated speed of the basic CGT. This paper consists of the current state of development of the CGT302 and how ceramic components are applied.

Sign in / Sign up

Export Citation Format

Share Document