AGT101 Advanced Gas Turbine Technology Update

1986 ◽  
Author(s):  
G. L. Boyd ◽  
J. R. Kidwell ◽  
D. M. Kreiner
Keyword(s):  
Gas Turbine ◽  
Technology Development ◽  
Development Program ◽  
Turbine Rotor ◽  
Test Time ◽  
Inlet Temperature ◽  
Metal Foil ◽  
Steady State Operation ◽  
Full Speed ◽  
Engine Testing

The Garrett/Ford Advanced Gas Turbine Technology Development Program, designated AGT101, has made significant progress during 1985 encompassing ceramic engine and ceramic component testing. Engine testing has included full speed operation to 100,000 rpm and 1149C (2100F) turbine inlet temperature, initial baseline performance mapping and ceramic combustor start and steady state operation. Over 380 hours of test time have been accumulated on four development engines. High temperature foil bearing coatings have passed rig test and a thick precious metal foil coating selected for engine evaluation. Ceramic structures have been successfully rig tested at 1371C (2500F) for over 27 hours. Interface compatibility testing conducted during these runs indicate RBSN-to-RBSN or SASC-to-SASC result in “sticking” — however, RBSN-to-SASC in either planar or line contact show no evidence of sticking. Ceramic combustor rig tests have demonstrated acceptable lightoffs using either a conventional ignitor or a commercially available glow plug. Operation to 1371C (2500F) combustor discharge temperatures have also been demonstrated. Ceramic turbine rotor fabrication efforts have continued at ACC and Ford. Kyocera and NGK-Locke also have been working on the rotor. Several rotors have been received and are currently undergoing final machining and qualification tests. Testing of the all-ceramic AGT101 engine is currently scheduled for late 1985.

scholarly journals Current Status of Ceramic Gas Turbine (CGT302)

1998 ◽  
Author(s):  
Hirotake Kobayashi ◽  
Tetsuo Tatsumi ◽  
Takashi Nakashima ◽  
Isashi Takehara ◽  
Yoshihiro Ichikawa
Keyword(s):  
Gas Turbine ◽  
Thermal Efficiency ◽  
Technology Development ◽  
Development Program ◽  
Point Of View ◽  
Current Status ◽  
Fiscal Year ◽  
Inlet Temperature ◽  
Development Organization ◽  
New Energy

In Japan, from the point of view of energy saving and environmental protection, a 300kW Ceramic Gas Turbine (CGT) Research and Development program started in 1988 and is still continuing as a part of “the New Sunshine Project” promoted by the Ministry of International Trade and Industry (MITT). The final target of the program is to achieve 42% thermal efficiency at 1350°C of turbine inlet temperature (TIT) and to keep NOx emissions below present national regulations. Under contract to the New Energy and Industrial Technology Development Organization (NEDO), Kawasaki Heavy Industries, Ltd. (KHI) has been developing the CGT302 with Kyocera Corporation and Sumitomo Precision Products Co., Ltd. By the end of the fiscal year 1996, the CGT302 achieved 37.0% thermal efficiency at 1280°C of TIT. In 1997, TIT reached 1350°C and a durability operation for 20 hours at 1350°C was conducted successfully. Also fairly low NOx was proved at 1300°C of TIT. In January 1998, the CGT302 has achieved 37.4% thermal efficiency at 1250°C TIT. In this paper, we will describe our approaches to the target performance of the CGT302 and current status.

scholarly journals Status of the Automotive Ceramic Gas Turbine Development Program: Year 3 Progress

1994 ◽  
Author(s):  
Takane Itoh ◽  
Hidetomo Kimura
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Performance Test ◽  
Development Program ◽  
Turbine Rotor ◽  
Maximum Speed ◽  
Inlet Temperature ◽  
Test Rig ◽  
Thermal Test ◽  
The Individual

Under the ongoing seven-year program, designated “Research and Development of Automotive Ceramic Gas Turbine Engine (CGT Program)”, started in June 1990. Japan Automobile Research Institute. Inc. (JARI) is continuing to address the issues of developing and demonstrating the advantageous potentials of ceramic gas turbines for automotive use. This program has been conducted by the Petroleum Energy Center (PEC) with the financial support of MITI. The basic engine is a 100 kW, single-shaft regenerative engine having a turbine inlet temperature of 1350°C and a rotor speed of 110,000 rpm. In the third year of this program, the experimental evaluation of the individual engine components and various assembly tests in a static thermal test rig were continued. Exhaust emissions were also measured in a performance test rig for an initially designed pre-mixed, pre-vaporized lean (PPL) combustor. A maximum speed of 130,700 rpm was obtained during hot spin tests of delivered ceramic turbine rotors, which was almost the same level as during cold spin tests. A dynamic thermal test including a centrifugal compressor, a ceramic radial turbine rotor and all the ceramic stationary hot parts was initiated.

scholarly journals AGT101 Advanced Gas Turbine Technology Update

1984 ◽  
Author(s):  
J. R. Kidwell ◽  
D. M. Kreiner ◽  
R. A. Rackley ◽  
J. L. Mason
Keyword(s):  
United States ◽  
Gas Turbine ◽  
The United States ◽  
Turbine Rotor ◽  
Department Of Energy ◽  
Screening Tests ◽  
Inlet Temperature ◽  
United States Department ◽  
Turbine Engine ◽  
Engine Testing

The Garrett/Ford Advanced Gas Turbine (AGT) Technology Project, authorized under NASA Contract DEN3-167, is sponsored by and is part of the United States Department of Energy Gas Turbine Highway Vehicle System Program. Program effort is oriented at providing the United States automotive industry the high risk long-range technology necessary to produce gas turbine powertrains for automobiles that will have reduced fuel consumption and reduced environmental impact. The AGT101 power section is a 74.6 kW (100 hp), regenerated single-shaft gas turbine engine operating at a maximum turbine inlet temperature of 1371°C (2500°F). Maximum rotor speed is 10,472 rad/sec (100,000 rpm). All high temperature components, including the turbine rotor, are ceramic. Development has progressed through aerothermodynamic testing of all components with compressor and turbine performance goals achieved. Some 200 hours of AGT101 testing has been accumulated at a nominal 871°C (1600°F) on three metal engines. Individual and collective ceramic component screening tests have been successfully accomplished at temperatures up to 1149°C (2100°F). Ceramic turbine rotors have been successfully cold spun to the required proof speed of 12,043 rad/sec (115,000 rpm), a 15-percent overspeed, and subjected to dynamic thermal shock tests simulating engine conditions. Engine testing of the ceramic structures and of the ceramic turbine rotor is planned in the near future.

scholarly journals Status of the Automotive Ceramic Gas Turbine Development Program: Year 2 Progress

1993 ◽  
Author(s):  
Takane Itoh ◽  
Hidetomo Kimura
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
High Speed ◽  
Development Program ◽  
Turbine Rotor ◽  
Inlet Temperature ◽  
Turbine Inlet Temperature ◽  
Turbine Engine ◽  
Basic Engine ◽  
Second Year

A seven-year program, designated “Research & Development of Automotive Ceramic Gas Turbine Engine (CGT Program)”, was started in June 1990 with the object of demonstrating the advantageous potentials of ceramic gas turbines for automotive use. This CGT-Program is conducted by PEC with the support of MITI. The basic engine is a 100-kW, single-shaft engine having a turbine inlet temperature of a 1350°C and a rotor speed of 110,000 rpm. During the second year of the program, experimental evaluation of the various components was started, including a centrifugal compressor, a radial turbine rotor, a high speed rotor system and initial ceramic hot parts. Cold and hot spin testing of ceramic rotors from three different ceramic suppliers was also initiated.

scholarly journals Ceramic Stationary Gas Turbine Development Program — Design and Test of a First Stage Ceramic Nozzle

1998 ◽  
Author(s):  
Leslie Faulder ◽  
John McClain ◽  
Bryan Edwards ◽  
Vijay Parthasarathy
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Fuel Efficiency ◽  
Development Program ◽  
The United States ◽  
Turbine Rotor ◽  
Department Of Energy ◽  
Inlet Temperature ◽  
United States Department ◽  
Engine Test

The goal of the Ceramic Stationary Gas Turbine(CSGT) Development Program, under the sponsorship of the United States Department of Energy (DOE), Office of Industrial Technologies (OIT), is to improve the performance (fuel efficiency, output power, exhaust emissions) of stationary gas turbines in cogeneration through the selective replacement of hot section components with ceramic parts. Phase II of this program includes detailed engine and component design, procurement and testing. This paper will review the design and test of the first stage ceramic nozzle for the Centaur 50S engine. For this test an uncooled monolithic ceramic nozzle made from SN-88 silicon nitride(NGK Insulators Ltd.) was used. A major challenge in the successful introduction of ceramic parts into a gas turbine is the design of the interface between the ceramic parts and metallic components. The design and attachment of the ceramic nozzle was greatly influenced by these considerations. Metallic components in the stationary structure of the turbine have been added or redesigned to retrofit the ceramic nozzle into the all metallic Centaur 50S engine. This paper will also discuss special handling and assembly techniques used to install the ceramic nozzle into the engine. Trial assemblies were used in the engine build process, this proved most beneficial in identifying problems and reducing the risk of damage to the ceramic nozzles. Assembly techniques were designed to reduce assembly loads and to eliminate blind assemblies. Before installing any ceramic nozzles into the engine they were first required to successfully pass both mechanical and thermal proof tests. Details of these proof tests and the final full load engine test will be described in this paper. The engine test was run at a turbine rotor inlet temperature(TRIT) of 1010°C. Total number of engine starts was six, and the total run time was approximately 10 hours.

scholarly journals USN Land Based Testing of the WR21 ICR Gas Turbine

1999 ◽  
Author(s):  
Robin W. Parry ◽  
Edward House ◽  
Matthew Stauffer ◽  
Michael Iacovelli ◽  
William J. Higgins
Keyword(s):  
Gas Turbine ◽  
Systems Engineering ◽  
Development Program ◽  
Test Site ◽  
Test Facility ◽  
Endurance Test ◽  
Test Program ◽  
The Us ◽  
Test House ◽  
Engine Testing

Development of the Northrop Grumman / Rolls-Royce WR21 Intercooled Recuperated (ICR) Gas Turbine, begun in 1992, is now well advanced and system testing has been completed on eight engine builds at the Royal Navy’s Admiralty Test House located at the Defence Evaluation and Research Agency, Pyestock in the United Kingdom. Test activity is shortly to move to the US Navy’s Test Site at the Naval Surface Warfare Center, Carderock Division – Ship Systems Engineering Station in Philadelphia, PA, where a new test facility has been built to carry out some final development testing and an endurance test. A previous paper on this subject (94-GT-186) defined a test program leading to a design review and the beginning of Qualification Testing. The development program has since evolved and it is the aim of this paper to summarize engine testing to date and set out the plan for conclusion of development testing. The paper will describe the development of the Philadelphia Test Site, as a combined site for the US Navy’s Integrated Power System (IPS) and ICR testing. This will include a description of the advanced, high-accuracy Data Acquisition System (DAS). Finally, the test program and the development and endurance test objectives will be outlined.

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.

Micro Gas Turbine With Ceramic Nozzle and Rotor

2005 ◽  
Author(s):  
Takayuki Matsunuma ◽  
Hiro Yoshida ◽  
Norihiko Iki ◽  
Takumi Ebara ◽  
Satoshi Sodeoka ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Turbine Rotor ◽  
Total Power ◽  
Inlet Temperature ◽  
Present System ◽  
Outlet Temperature ◽  
Micro Gas Turbine ◽  
Buffer Material ◽  
Inconel 713C

A series of operation tests of a ceramic micro gas turbine has been successfully carried out. The baseline machine is a small single-shaft turbojet engine (J-850, Sophia Precision Corp.) with a centrifugal compressor, an annular type combustor, and a radial turbine. As a first step, an Inconel 713C alloy turbine rotor of 55 mm in diameter was replaced with a ceramic rotor (SN-235, Kyocera Corporation). A running test was conducted at rotational speeds of up to 140,000 rpm in atmospheric air. At this rotor speed, the compression pressure ratio and the thrust were 3 and 100 N, respectively. The total energy level (enthalpy and kinetic energy) of the exhaust gas jet was 240 kW. If, for example, it is assumed that 10% of the total power of the exhaust jet gas was converted into electricity, the present system would correspond to a generator with 24 kW output power. The measured turbine outlet temperature was 950°C (1,740°F) and the turbine inlet temperature was estimated to be 1,280°C (2,340°F). Although the ceramic rotor showed no evidence of degradation, the Inconel nozzle immediately in front of the turbine rotor partially melted in this rotor condition. As a second step, the Inconel turbine nozzle and casing were replaced with ceramic parts (SN-01, Ohtsuka Ceramics Inc.). The ceramic nozzle and case were supported by metal parts. Through tests with the ceramic nozzle, it became evident that one of the key technologies for the development of ceramic gas turbines is the design of the interface between the ceramic components and the metallic components, because the difference between the coefficients of linear thermal expansion of the ceramic and metal produces large thermal stress at their interface in the high-temperature condition. A buffer material made of alumina fiber was therefore introduced at the interface between the ceramic and metal.

Water-Cooled Gas Turbine Technology Development: Fuels Flexibility

1979 ◽  
Author(s):  
M. W. Horner ◽  
W. H. Day ◽  
D. P. Smith ◽  
A. Cohn
Keyword(s):  
Gas Turbine ◽  
Technology Development ◽  
Development Program ◽  
Open Circuit ◽  
Model Verification ◽  
Small Scale ◽  
Water Cooling ◽  
Gas Temperature ◽  
Pressurized Water ◽  
Early Results

A continuing technology development program initiated by General Electric (GE) in the early 1960s and joined by the Electric Power Research Institute (EPRI) in 1974 is successfully resolving potential barrier problems in the development of water cooled turbines. Early work by GE Corporate Research and Development demonstrated the feasibility of closed circuit, pressurized water-cooling of stationary nozzles (vanes), and of open circuit, unpressurized water-cooling of rotating buckets (blades). A small-scale turbine was designed, fabricated, and operated at a gas temperature of 2850 F (1565 C) at 16 atm, with surface metal temperatures less than 1000 F (540 C). Early results from the EPRI sponsored Water-Cooled Gas Turbine Development Programs were presented at the 1978 Gas Turbine Conference (Report #ASME 78-GT-72). This paper reports more recent results, obtained between mid-1977 and mid-1978. Significant progress has been made in a number of areas: (a) water-cooled nozzle and bucket design and fabrication, (b) corrosion kinetics model verification and testing, (c) partially filled internal channel bucket heat transfer testing, and (d) stationary to rotating water transfer and collection testing. Results to date are encouraging with regard to the application of water-cooled turbine components to achieve improved reliability and fuels flexibility at increased turbine firing temperatures.

Development of 300kW Class Ceramic Gas Turbine (CGT303)

1994 ◽  
Author(s):  
Issel Ohhashi ◽  
Sadao Arakawa
Keyword(s):  
Gas Turbine ◽  
Technology Development ◽  
Maximum Output Power ◽  
Development Program ◽  
Maximum Output ◽  
Power Generator ◽  
Construction Machinery ◽  
Development Organization ◽  
New Energy ◽  
Ceramic Components

CCT303 is a two-shaft regenerative ceramic gas turbine with rotary heat exchangers for the purpose of mobile power generator. It is also widely adaptable for industrial machinery and construction machinery as well. The development program of CGT303 is funded by New Energy and Industrial Technology Development Organization (NEDO). The maximum output power of 300kW and thermal efficiency of 42% at TiT 1350C are the objectives of this development. The high TiT requires for the material of all gas passage components to use ceramics which are designed appropriately to keep sufficient strength by using sophisticated computer analysis. Hot spin tests on ceramic turbine rotors and thermal shock tests on stationary ceramic components have been carried out to prove their strength. The paper covers the design concept of CGT303 and results of analysis.

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