Component and Procedural Improvements for the T-62T-40-7 Gas Turbine in the LCAC Fleet

1996 ◽  
Vol 118 (2) ◽  
pp. 369-374
Author(s):  
J. P. Ehrhardt ◽  
S. K. Spring
Keyword(s):  
Power Systems ◽  
Gas Turbine ◽  
Environmental Conditions ◽  
Operating Time ◽  
Auxiliary Power Unit ◽  
Auxiliary Power ◽  
Marine Application ◽  
Air Cushion ◽  
Component Failures ◽  
The U.S

The Sundstrand Power Systems T-62T-40-7 Gas Turbine Auxiliary Power Unit (APU) was adapted from an aircraft-borne APU to a marine application on the U.S. Navy’s Landing Craft Air Cushion (LCAC). Although the LCAC APU experienced less operating time than its aircraft version, the environmental conditions that exist cause unusual wear and component failures. Component and procedural improvements have been developed to extend the reliability of the T-62T-40-7 on board the LCAC.

scholarly journals Component and Procedural Improvements for the T-62T-40-7 Gas Turbine in the LCAC Fleet

1994 ◽  
Author(s):  
Jerome P. Ehrhardt ◽  
Soren K. Spring
Keyword(s):  
Power Systems ◽  
Gas Turbine ◽  
Environmental Conditions ◽  
Operating Time ◽  
Auxiliary Power Unit ◽  
Auxiliary Power ◽  
Marine Application ◽  
Air Cushion ◽  
Component Failures ◽  
The U.S

The Sundstrand Power Systems T-62T-40-7 Gas Turbine Auxiliary Power Unit (APU) was adapted from an aircraft-borne APU to a marine application on the U.S. Navy’s Landing Craft Air Cushion (LCAC). Although the LCAC APU experienced less operating time than its aircraft version, the environmental conditions that exist cause unusual wear and component failures. Component and procedural improvements have been developed to extend the reliability of the T-62T-40-7 on board the LCAC.

scholarly journals Gemini T-20G-8 XM1 Tank APU

1981 ◽  
Author(s):  
C. Rodgers ◽  
J. Zeno ◽  
E. A. Drury ◽  
A. Karchon
Keyword(s):  
Gas Turbine ◽  
Power Unit ◽  
Weather Conditions ◽  
Cold Weather ◽  
Turbine Engine ◽  
Auxiliary Power Unit ◽  
Auxiliary Power ◽  
Generator Sets ◽  
Main Engine ◽  
The U.S

Auxiliary power is often provided on combat vehicles in the U.S. Army for battery charging, operation of auxiliary vehicle equipment when the main engine is not running, or to provide assistance in starting the main engine in extreme cold weather conditions. The use of a gas turbine for these applications is particularly attractive, due to its small size and lightweight. In November 1978, the U.S. Army Tank-Automotive Research and Development Command, Warren, MI awarded a contract to the Turbomach Division of Solar Turbines International, San Diego, CA, for the development of a 10 kW 28 vdc gas turbine powered auxiliary power unit (APU) for installation in the XM1 main battle tank. This paper describes the general features of the Solar Turbomach T-20G-8 Auxiliary Power Unit, a single-shaft gas turbine driven generator set which has been developed under this contract. This APU is one of the family of Gemini powered APUs and is a derivative of the U.S. Army 10 kW gas turbine engine-driven, 60 and 400 Hz generator sets developed by Solar. The electrical components were newly developed for this particular application. Currently, the APU is in qualification testing both in the laboratory and in the XM1 main battle tank.

scholarly journals Experience With the TF40B Engine in the LCAC Fleet

1992 ◽  
Author(s):  
Edward M. House
Keyword(s):  
Gas Turbine ◽  
Hot Corrosion ◽  
Compressor Blade ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Improvement Program ◽  
Air Cushion ◽  
Engine Components ◽  
Carbon Erosion ◽  
The U.S

Four Textron Lycoming TF40B marine gas turbine engines are used to power the U.S. Navy’s Landing Craft Air Cushion (LCAC) vehicle. This is the first hovercraft of this configuration to be put in service for the Navy as a landing craft. The TF40B has experienced compressor blade pitting, carbon erosion of the first turbine blade and hot corrosion of the hot section. Many of these problems were reduced by changing the maintenance and operation of the LCAC. A Component Improvement Program (CIP) is currently investigating compressor and hot section coatings better suited for operation in a harsh marine environment. This program will also improve the performance of some engine components such as the bleed manifold and bearing seals.

Low-Emissions Technology Development for Auxiliary Power Unit Combustion Systems

2021 ◽  
Author(s):  
Thomas Bronson ◽  
Rudy Dudebout ◽  
Nagaraja Rudrapatna
Keyword(s):  
Gas Turbine ◽  
Power Unit ◽  
Fuel Injection ◽  
Oxides Of Nitrogen ◽  
Combustion System ◽  
Auxiliary Power Unit ◽  
Criteria Pollutants ◽  
Auxiliary Power ◽  
Combustion Systems ◽  
Aircraft Application

Abstract The aircraft Auxiliary Power Unit (APU) is required to provide power to start the main engines, conditioned air and power when there are no facilities available and, most importantly, emergency power during flight operation. Given the primary purpose of providing backup power, APUs have historically been designed to be extremely reliable while minimizing weight and fabrication cost. Since APUs are operated at airports especially during taxi operations, the emissions from the APUs contribute to local air quality. There is clearly significant regulatory and public interest in reducing emissions from all sources at airports, including from APUs. As such, there is a need to develop technologies that reduce criteria pollutants, namely oxides of nitrogen (NOx), unburned hydrocarbons (UHC), carbon monoxide (CO) and smoke (SN) from aircraft APUs. Honeywell has developed a Low-Emissions (Low-E) combustion system technology for the 131-9 and HGT750 family of APUs to provide significant reduction in pollutants for narrow-body aircraft application. This article focuses on the combustor technology and processes that have been successfully utilized in this endeavor, with an emphasis on abating NOx. This paper describes the 131-9/HGT750 APU, the requirements and challenges for small gas turbine engines, and the selected strategy of Rich-Quench-Lean (RQL) combustion. Analytical and experimental results are presented for the current generation of APU combustion systems as well as the Low-E system. The implementation of RQL aerodynamics is well understood within the aero-gas turbine engine industry, but the application of RQL technology in a configuration with tangential liquid fuel injection which is also required to meet altitude ignition at 41,000 ft is the novelty of this development. The Low-E combustion system has demonstrated more than 25% reduction in NOx (dependent on the cycle of operation) vs. the conventional 131-9 combustion system while meeting significant margins in other criteria pollutants. In addition, the Low-E combustion system achieved these successes as a “drop-in” configuration within the existing envelope, and without significantly impacting combustor/turbine durability, combustor pressure drop, or lean stability.

Fiber Metal Acoustic Material for Gas Turbine Exhaust Environments

1989 ◽  
Vol 111 (1) ◽  
pp. 181-185
Author(s):  
M. S. Beaton
Keyword(s):  
Gas Turbine ◽  
Power Unit ◽  
Broad Band ◽  
Acoustic Energy ◽  
Acoustic Properties ◽  
Roll Forming ◽  
Sound Waves ◽  
Auxiliary Power Unit ◽  
Auxiliary Power ◽  
Fiber Metal

FELTMETAL® fiber metal acoustic materials function as broad band acoustic absorbers. Their acoustic energy absorbance occurs through viscous flow losses as sound waves pass through the tortuous pore structure of the material. A new FELTMETAL® fiber metal acoustic material has been designed for use in gas turbine auxiliary power unit exhaust environments without supplemental cooling. The physical and acoustic properties of FM 827 are discussed. Exposure tests were conducted under conditions that simulated auxiliary power unit operation. Weight gain and tensile strength data as a function of time of exposure at 650°C (1202°F) are reported. Fabrication of components with fiber metal acoustic materials is easily accomplished using standard roll forming and gas tungsten arc welding practices.

scholarly journals Method of coordinating air starter and auxiliary power unit joint operation

2020 ◽  
pp. 5-13
Author(s):  
Grigory Popov ◽  
◽  
Vasily Zubanov ◽  
Valeriy Matveev ◽  
Oleg Baturin ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Power Unit ◽  
Gas Turbine Engine ◽  
Working Process ◽  
Joint Operation ◽  
Turbine Engine ◽  
Auxiliary Power Unit ◽  
Auxiliary Power ◽  
Start Up ◽  
Air Turbine

The presented work provides a detailed description of the method developed by the authors for coordinating the working process of the main elements of the starting system for a modern gas turbine engine for a civil aviation aircraft: an auxiliary power unit (APU) and an air turbine – starter. This technique was developed in the course of solving the practical problem of selecting the existing APU and air turbine for a newly created engine. The need to develop this method is due to the lack of recommendations on the coordination of the elements of the starting system in the available literature. The method is based on combining the characteristics of the APU and the turbine, reduced to a single coordinate system. The intersection of the characteristic’s lines corresponding to the same conditions indicates the possibility of joint operation of the specified elements. The lack of intersection indicates the impossibility of joint functioning. The calculation also takes into account losses in the air supply lines to the turbine. The use of the developed method makes it possible to assess the possibility of joint operation of the APU and the air turbine in any operating mode. In addition to checking the possibility of functioning, as a result of the calculation, specific parameters of the working process at the operating point are determined, which are then used as initial data in calculating the elements of the starting system, for example, determining the parameters of the turbine, which in turn allow providing initial information for calculating the starting time or the possibility of functioning of the starting system GTE according to strength and other criteria. The algorithm for calculating the start-up time of the gas turbine engine was also developed by the authors and implemented in the form of an original computer program. Keywords: gas turbine engine start-up, GTE starting system, air turbine, methodology, joint work, auxiliary power unit, power, start-up time, characteristics matching, coordination, operational characteristics, computer program.

Technological analysis and fuel consumption saving potential of different gas turbine thermodynamic configurations for series hybrid electric vehicles

2019 ◽  
Vol 234 (6) ◽  
pp. 1544-1562
Author(s):  
Wissam Bou Nader ◽  
Yuan Cheng ◽  
Emmanuel Nault ◽  
Alexandre Reine ◽  
Samer Wakim ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Fuel Consumption ◽  
Electric Vehicle ◽  
Power Unit ◽  
Hybrid Electric Vehicle ◽  
Auxiliary Power Unit ◽  
Auxiliary Power ◽  
Series Hybrid Electric Vehicle ◽  
Hybrid Electric ◽  
Technological Analysis

Gas turbine systems are among potential energy converters to substitute the internal combustion engine as auxiliary power unit in future series hybrid electric vehicle powertrains. Fuel consumption of these auxiliary power units in the series hybrid electric vehicle strongly relies on the energy converter efficiency and power-to-weight ratio as well as on the energy management strategy deployed on-board. This paper presents a technological analysis and investigates the potential of fuel consumption savings of a series hybrid electric vehicle using different gas turbine–system thermodynamic configurations. These include a simple gas turbine, a regenerative gas turbine, an intercooler regenerative gas turbine, and an intercooler regenerative reheat gas turbine. An energetic and technological analysis is conducted to identify the systems’ efficiency and power-to-weight ratio for different operating temperatures. A series hybrid electric vehicle model is developed and the different gas turbine–system configurations are integrated as auxiliary power units. A bi-level optimization method is proposed to optimize the powertrain. It consists of coupling the non-dominated sorting genetic algorithm to the dynamic programming to minimize the fuel consumption and the number of switching ON/OFF of the auxiliary power unit, which impacts its durability. Fuel consumption simulations are performed on the worldwide-harmonized light vehicles test cycle while considering the electric and thermal comfort vehicle energetic needs. Results show that the intercooler regenerative reheat gas turbine–auxiliary power unit presents an improved fuel consumption compared with the other investigated gas turbine systems and a good potential for implementation in series hybrid electric vehicles.

Integration of Flame-Assisted Fuel Cells With a Gas Turbine Running Jet-A As Fuel

2019 ◽  
Author(s):  
Rhushikesh Ghotkar ◽  
Ryan J. Milcarek
Keyword(s):  
Fuel Cells ◽  
Solid Oxide Fuel Cells ◽  
Gas Turbine ◽  
Equilibrium Analysis ◽  
Aircraft Industry ◽  
Dual Chamber ◽  
Auxiliary Power Unit ◽  
Auxiliary Power ◽  
Chemical Equilibrium Analysis ◽  
Design Power

Abstract In recent years, the aircraft industry is heading towards the concept of the More Electric Airplane (MEA). Previous research has investigated the possibility of integrating Dual Chamber Solid Oxide Fuel Cells (DC-SOFC) with the auxiliary power unit (APU) of the aircraft. This paper evaluates the merits of integrating the recently proposed Flame-assisted Fuel Cells (FFCs) with the APU gas turbine system. The syngas composition for fuel-rich combustion is studied using chemical equilibrium analysis of Jet-A/air at 8 Bar and 1073 K. The results show the potential for reforming Jet-A fuel to 22% Carbon Monoxide and 18% Hydrogen in the exhaust at an equivalence ratio of 2.4. The paper also reports how the efficiency of power generation changes when FFCs are placed in the combustor of a turbine in the APU. The maximum theoretical electrical efficiency of the FFC/combustor and the area and weight of the fuel cell required to generate the design power is calculated. The FFC offers a viable substitute for the DC-SOFC to be integrated with the APU.

An auxiliary power unit for advanced aircraft electric power systems

2015 ◽  
Vol 119 ◽  
pp. 393-406 ◽  
Author(s):  
Hadi Ebrahimi ◽  
Javad R. Gatabi ◽  
Hassan El-Kishky
Keyword(s):  
Power Systems ◽  
Electric Power ◽  
Power Unit ◽  
Electric Power Systems ◽  
Auxiliary Power Unit ◽  
Auxiliary Power
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