scholarly journals System Development Test Program for the WR-21 Intercooled Recuperated (ICR) Gas Turbine Engine System

1994 ◽  
Author(s):  
William J. Hawkins ◽  
Douglas Mathieson ◽  
Chris J. Bruce ◽  
Paul Socoloski
Keyword(s):  
Gas Turbine ◽  
System Development ◽  
Test Site ◽  
The United States ◽  
Gas Turbine Engine ◽  
Test Bed ◽  
Site Location ◽  
Test Program ◽  
Turbine Engine ◽  
Engine System

Westinghouse Electric Corporation has teamed with Rolls-Royce to develop an affordable, commercially based Intercooled/Recuperated Gas Turbine Engine System (ICR) for the United States Navy. This engine system known as WR-21 will become the next prime mover on Navy new construction surface combatants. The system development test program for the WR-21 engine system will be carried out at two test sites in geographically different locations. These are the US Navy’s Test Site at the Carderock Division Naval Surface Warfare Center in Philadelphia, Pa. and the Royal Navy’s Admiralty Test House at the Test and Evaluation Establishment, Pyestock in the United Kingdom. This paper will briefly describe the WR-21 engine system with a more detailed discussion of the system development test program itself. This will include descriptions of the system development testing to be performed and the test facilities and data acquisition systems at each test site location. Also discussed are the methods used to establish the required design commonality between each test site to establish test bed cross-calibration and provide test program flexibility and interchangeability of testing at each site.

WR21 Water Wash Development Approach for the Intercooled Recuperated (ICR) Gas Turbine Engine

1997 ◽  
Author(s):  
Jay T. Janton ◽  
Kevin Widdows
Keyword(s):  
Gas Turbine ◽  
Development Program ◽  
Test Site ◽  
Gas Turbine Engine ◽  
Test Program ◽  
Turbine Engine ◽  
Baseline Design ◽  
Development Approach ◽  
Pressure Compressor ◽  
Wash Test

The WR21 Intercooled Recuperated (ICR) Gas Turbine Engine is being developed as the prime power plant for future US and Foreign Navy ship applications. The development test program started in July 1994 and is still ongoing. One of the many challenges of the ICR design is the development of the compressors and intercooler (IC) wash system. The integration of the IC between the intermediate pressure compressor (IPC) and high pressure compressor (HPC) is unique to current US Navy applications and has introduced new design considerations from traditional wash development programs that must be addressed. Significant increase in wetted surface area of the heat exchanger (HX) matrix and the radial flow are two design aspects unique to the WR21. This paper reviews the design of the WR21 engine and the challenges it offers to developing both crank and on-line compressor/IC wash systems. The baseline design of the water wash systems are discussed, in addition to the water wash test program and its integration into the overall WR2I development program. Details are also given of the off-engine wash delivery system and salt injection systems in place at the test site. Crank wash test results to date are also presented.

The Navy 500-Hour Test (NFHT) of the Intercooled Recuperated Gas Turbine Engine System (ICR)

2001 ◽  
Author(s):  
Carl P. Grala ◽  
Edward M. House
Keyword(s):  
Gas Turbine ◽  
United States Navy ◽  
Operating Time ◽  
The United States ◽  
Gas Turbine Engine ◽  
Prime Mover ◽  
Turbine Engine ◽  
Major Development ◽  
Qualification Testing ◽  
Engine System

The Intercooled Recuperated Gas Turbine Engine System (ICR) is being developed by the United States Navy (USN) for shipboard application as a prime mover. The major development goal of the program is reduced fuel consumption relative to the LM2500, the current fielded gas turbine prime mover. This paper describes a 500-hour endurance test of the ICR system. The test was conducted at Naval Surface Warfare Center Carderock Division (NSWCCD), Philadelphia, in accordance with USN requirements which mimicked the qualification requirements for the system. Data to assess the capability of the ICR to pass the qualification test was collected. Overall, the ICR has demonstrated a readiness to commence qualification testing. The ICR completed the test with a total accumulated operating time of 457 hours and total endurance time of 322 hours. Achievement of the planned 500 endurance hours was precluded by persistent facility waterbrake problems.

Case Closed: The Completion of the United States Navy 501-K34 Gas Turbine Engine RADCON Program (2011 - 2019)

2021 ◽  
Author(s):  
Jeffrey S. Patterson ◽  
Kevin Fauvell ◽  
Dennis Russom ◽  
Willie A. Durosseau ◽  
Phyllis Petronello ◽  
...  
Keyword(s):  
United States ◽  
Gas Turbine ◽  
United States Navy ◽  
The United States ◽  
Gas Turbine Engine ◽  
United States Government ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Turbine Engine ◽  
The U.S

Abstract The United States Navy (USN) 501-K Series Radiological Controls (RADCON) Program was launched in late 2011, in response to the extensive damage caused by participation in Operation Tomodachi. The purpose of this operation was to provide humanitarian relief aid to Japan following a 9.0 magnitude earthquake that struck 231 miles northeast of Tokyo, on the afternoon of March 11, 2011. The earthquake caused a tsunami with 30 foot waves that damaged several nuclear reactors in the area. It was the fourth largest earthquake on record (since 1900) and the largest to hit Japan. On March 12, 2011, the United States Government launched Operation Tomodachi. In all, a total of 24,000 troops, 189 aircraft, 24 naval ships, supported this relief effort, at a cost in excess of $90.0 million. The U.S. Navy provided material support, personnel movement, search and rescue missions and damage surveys. During the operation, 11 gas turbine powered U.S. warships operated within the radioactive plume. As a result, numerous gas turbine engines ingested radiological contaminants and needed to be decontaminated, cleaned, repaired and returned to the Fleet. During the past eight years, the USN has been very proactive and vigilant with their RADCON efforts, and as of the end of calendar year 2019, have successfully completed the 501-K Series portion of the RADCON program. This paper will update an earlier ASME paper that was written on this subject (GT2015-42057) and will summarize the U.S. Navy’s 501-K Series RADCON effort. Included in this discussion will be a summary of the background of Operation Tomodachi, including a discussion of the affected hulls and related gas turbine equipment. In addition, a discussion of the radiological contamination caused by the disaster will be covered and the resultant effect to and the response by the Marine Gas Turbine Program. Furthermore, the authors will discuss what the USN did to remediate the RADCON situation, what means were employed to select a vendor and to set up a RADCON cleaning facility in the United States. And finally, the authors will discuss the dispensation of the 501-K Series RADCON assets that were not returned to service, which include the 501-K17 gas turbine engine, as well as the 250-KS4 gas turbine engine starter. The paper will conclude with a discussion of the results and lessons learned of the program and discuss how the USN was able to process all of their 501-K34 RADCON affected gas turbine engines and return them back to the Fleet in a timely manner.

The AGT101 Advanced Automotive Gas Turbine

1982 ◽  
Author(s):  
R. A. Rackley ◽  
J. R. Kidwell
Keyword(s):  
United States ◽  
Gas Turbine ◽  
The United States ◽  
Gas Turbine Engine ◽  
Development Project ◽  
Single Stage ◽  
Department Of Energy ◽  
Inlet Temperature ◽  
United States Department ◽  
Turbine Engine

The Garrett/Ford Advanced Gas Turbine Powertrain System Development 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 technology base necessary to produce gas turbine powertrains competitive for automotive applications having: (1) reduced fuel consumption, (2) multi-fuel capability, and (3) low emissions. The AGT101 powertrain is a 74.6 kW (100 hp), regenerated single-shaft gas turbine engine operating at a maximum turbine inlet temperature of 1644 K (2500 °F), coupled to a split differential gearbox and Ford automatic overdrive production transmission. The gas turbine engine has a single-stage centrifugal compressor and a single-stage radial inflow turbine mounted on a common shaft. Maximum rotor speed is 10,472 rad/sec (100,000 rpm). All high-temperature components, including the turbine rotor, are ceramic. AGT101 powertrain development has been initiated, with testing completed on many aerothermodynamic components in dedicated test rigs and start of Mod I, Build 1 engine testing.

Development of the Ceramic Gas Turbine Engine System (CGT301)

1999 ◽  
Author(s):  
Takeshi Sakida ◽  
Shinya Tanaka ◽  
Takao Mikami ◽  
Masashi Tatsuzawa ◽  
Tomoki Taoka
Keyword(s):  
Gas Turbine ◽  
Turbine Blades ◽  
Gas Turbine Engine ◽  
Turbine Engine ◽  
The Future ◽  
Engine System ◽  
Primary Type ◽  
Three Phases

The CGT301 ceramic gas turbine has been developed under a contract from NEDO as a part of the New Sunshine Program of MITI since 1988 to 1998. The CGT301 is a recuperated, single-shaft ceramic gas turbine. Ceramic parts are used in the hot section of the engine, such as turbine blades, nozzle vanes, combustion liners and so on. As a primary feature of this turbine, the rotors are composed of ceramic blades inserted into metallic disks (“hybrid rotor”) for the future applicability to the large gas turbine. The R & D program consists of three phases, the model metal gas turbine, the primary type ceramic gas turbine and the pilot ceramic gas turbine. The pilot ceramic gas turbine showed etable operation at TIT of 1,350°C. This paper presents the progress in the development of the pilot ceramic gas turbine of CGT301.

Integration of the WR-21 Intercooled Recuperated Gas Turbine Into the Royal Navy Type 45 Destroyer

2001 ◽  
Author(s):  
Steven J. McCarthy ◽  
Ian Scott
Keyword(s):  
Gas Turbine ◽  
Distribution System ◽  
Life Cycle Cost ◽  
Electric Propulsion ◽  
Electrical Power ◽  
The United States ◽  
Gas Turbine Engine ◽  
Prime Mover ◽  
Royal Navy ◽  
Turbine Engine

The WR-21 gas turbine engine will be employed by the Royal Navy and potentially by the United States and French Navies in their future Integrated Full Electric Powered Surface Combatants. The WR-21 is an advanced cycle gas turbine that will not only meet the high power generator prime mover requirements of these ships but also offer an efficient cruise generator engine in one power dense package. The engine gives ship designers the freedom to procure, install and maintain one engine to power the vessel over its entire operating profile in place of the traditional two engine ‘cruise’ and ‘boost’ fit. Warship operators will also have a new freedom to configure the warship propulsion plant to return unprecedented Platform Life Cycle Cost reductions in peacetime while retaining operational capability in time of conflict. The Royal Navy is the first user of the WR-21 Intercooled and Recuperated (ICR) gas turbine engine in its Type 45 Area Defense destroyer. The vessel is a 6000 tonne monohull, fitted with an integrated electric propulsion plant comprising two WR-21 Gas Turbine Alternators (GTAs), the prime mover side of which are capable of delivering 25 MW (ISO) and the Alternator side of which is rated at 21.6 MWe (0.9 pf lagging), 4.16KVA. These GTAs in combination with a pair of diesel generators rated at around 2 MWe (0.9 pf lagging) will provide electrical power to two 20 MWe (0.9 pf lagging) 4.16 KVA electric propulsion motors and to the ship’s non propulsion consumer electrical distribution system. Any combination of generator set can provide any consumer with electrical power. This flexibility of propulsion plant configuration will demand a step change in operating culture if its ultimate benefits are to be truly harnessed. Every part of warship propulsion and gas turbine engine operating philosophy must be examined to check its relevance in the modern machinery outfit. The engines themselves must be scrutinized to ensure that they can fulfill the requirements of true ship generation machinery and are not regarded as ‘propulsion generators’. In a Warship that has only four sources of electrical power the principles of survivability and prime mover independence are fundamental.

Integrating Systems Engineering Into the USAF Academy Capstone Gas Turbine Engine Course

2011 ◽  
Vol 134 (2) ◽  
Author(s):  
August J. Rolling ◽  
Aaron R. Byerley ◽  
Charles F. Wisniewski
Keyword(s):  
Engineering Design ◽  
Gas Turbine ◽  
Air Force ◽  
Systems Engineering ◽  
Aircraft Engine ◽  
The United States ◽  
Gas Turbine Engine ◽  
Turbine Engine ◽  
Engine Design ◽  
Aeronautical Engineering

This paper is intended to serve as a template for incorporating technical management majors into a traditional engineering design course. In 2002, the Secretary of the Air Force encouraged the United States Air Force (USAF) Academy to initiate a new interdisciplinary academic major related to systems engineering. This direction was given in an effort to help meet the Air Force’s growing need for “systems” minded officers to manage the development and acquisition of its ever more complex weapons systems. The curriculum for the new systems engineering management (SEM) major is related to the “engineering of large, complex systems and the integration of the many subsystems that comprise the larger system” and differs in the level of technical content from the traditional engineering major. The program allows emphasis in specific cadet—selected engineering tracks with additional course work in human systems, operations research, and program management. Specifically, this paper documents how individual SEM majors have been integrated into aeronautical engineering design teams within a senior level capstone course to complete the preliminary design of a gas turbine engine. As the Aeronautical Engineering (AE) cadets performed the detailed engine design, the SEM cadets were responsible for tracking performance, cost, schedule, and technical risk. Internal and external student assessments indicate that this integration has been successful at exposing both the AE majors and the SEM majors to the benefits of “systems thinking” by giving all the opportunity to employ SE tools in the context of a realistic aircraft engine design project.

Telemetry System Integrated in a Small Gas Turbine Engine

2012 ◽  
Vol 134 (4) ◽  
Author(s):  
Stephen A Long ◽  
Stephen L Edney ◽  
Patrick A Reiger ◽  
Michael W Elliott ◽  
Frank Knabe ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Cooling System ◽  
Turbine Rotor ◽  
Gas Turbine Engine ◽  
Telemetry System ◽  
Test Program ◽  
Turbine Engine ◽  
Power Turbine ◽  
Successful Execution ◽  
Integration Effort

For the purpose of assessing combustion effects in a small gas turbine engine, there was a requirement to evaluate the rotating temperature and dynamic characteristics of the power turbine rotor module. This assessment required measurements be taken within the engine, during operation up to maximum power, using rotor mounted thermocouples and strain gauges. The acquisition of this data necessitated the use of a telemetry system that could be integrated into the existing engine architecture without affecting performance. As a result of space constraints, housing of the telemetry module was limited to placement in a hot section. To tolerate the high temperature environment, a cooling system was developed as part of the integration effort to maintain telemetry module temperatures within the limit allowed by the electronics. Finite element thermal analysis was used to guide the design of the cooling system. This was to ensure that sufficient airflow was introduced and appropriately distributed to cool the telemetry cavity, and hence electronics, without affecting the performance of the engine. Presented herein is a discussion of the telemetry system, instrumentation design philosophy, cooling system design and verification, and sample of the results acquired through successful execution of the full engine test program.

scholarly journals The Prototype of a 100-Mw, 3000 Rpm Gas Turbine Series for Power Generation

1974 ◽  
Author(s):  
G. P. Frigieri
Keyword(s):  
Power Generation ◽  
Control System ◽  
Gas Turbine ◽  
Peak Load ◽  
Gas Turbine Engine ◽  
Advanced Stage ◽  
Design Features ◽  
Test Program ◽  
Turbine Engine ◽  
Prototype Test

This paper presents the prototype of a large gas turbine new series whose peculiar characteristics make the same very attractive for both base and peak load applications. The gas turbine engine, now in an advanced stage of manufacturing, is scheduled to be bench tested in the last quarter of the year. The major design features of the gas turbine engine together with the prototype test program are described. In addition, the peculiar characteristics of the control system and and package installation are mentioned.

Sign in / Sign up

Export Citation Format

Share Document