scholarly journals GENERATION AND METHODS FOR VIBRO-ACOUSTIC ACTIVITY DECREASE IN GASCOMPRESSOR UNITS WITH GAS TURBINE DRIVE

2017 ◽  
Vol 2017 (1) ◽  
pp. 68-71
Author(s):  
Алексей Дроконов ◽  
Aleksey Drokonov ◽  
Алексей Дроконов ◽  
Aleksey Drokonov
Keyword(s):  
Gas Turbine ◽  
Centrifugal Compressor ◽  
Sound Field ◽  
Noise Pollution ◽  
Gas Turbine Engine ◽  
Noise Sources ◽  
Inlet System ◽  
Acoustic Characteristics ◽  
Turbine Engine ◽  
Air Inlet

Block-modular gas compressor units (GCU) of a container type with an aircraft and ship gasturbine drive – a power source of vibration and noise pollution of environment. Their basic inner sources – gas turbine engine and a centrifugal compressor. Besides, to power noise sources in the structure of GCU belong multiplier, an air cleaner of the air inlet system, an exhaust shaft, section walls of an engine and a compressor. A gas turbine engine and a compressor define mainly a distant sound field and the rest of noise sources – near-in one. A complex modernization of such plants may be carried out on the basis of the investigations of the level of vibrations and noise of all elements of such units. With this purpose there were carried out inves-tigations of vibro-acoustic characteristics of GCU of GCU-16MG type with the capacity of 16 MW where as a drive of the centrifugal compressor of 370-18-1 NZL type serves a ship convertible engine of DG-90 type produced by “Zarya” Co. Noise sources and vibrations of blade machines are studied, their vibro-acoustic characteristics are analyzed and methods for the decrease of vibro-acoustic activities of GCUs of such a type are offered.

Digital twin of rig for testing of centrifugal compressor for small-scale gas turbine engine

2021 ◽  
pp. 5-16
Author(s):  
Yu.М. Temis ◽  
A.V. Solovjeva ◽  
Yu.N. Zhurenkov ◽  
A.N. Startsev ◽  
M.Yu. Temis ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Centrifugal Compressor ◽  
Gas Turbine Engine ◽  
Small Scale ◽  
Turbine Engine ◽  
Digital Twin

Development and Testing of a Gas Turbine Engine Combustion Air Inlet Filtration System for the USMC Amphibious Combat Vehicle

2017 ◽  
Author(s):  
Thomai Gastopoulos ◽  
Joseph Lawton
Keyword(s):  
Gas Turbine ◽  
Marine Corps ◽  
Gas Turbine Engine ◽  
Bulk Water ◽  
Air Separation ◽  
United States Marine Corps ◽  
Turbine Engine ◽  
Air Inlet ◽  
Filtration System ◽  
Combat Vehicle

The Auxiliary Ships and New Acquisition Support Branch (Code 425) of the Naval Surface Warfare Center, Philadelphia Division conducted a study to assist the Marine Corps Systems Command in assessing the feasibility of using a gas turbine engine as a propulsion system on future United States Marine Corps Amphibious Combat Vehicles (ACV). The study was focused on developing and testing a gas turbine intake solution for the ACV that can remove saltwater from the intake airstream of a notional 3,000 horsepower ACV engine. Code 425 developed a two-part solution for the intake of the ACV. The first part of the solution is an intake shroud designed to elevate the intake to protect the engine from deck water wash. The second part of the solution is the Combustion Air Separation System (CASS), a gas turbine intake filtration system designed to remove marine contaminants that enter the intake. Code 425 tested a CASS prototype for its efficiency at removing saltwater spray and bulk water up to 10 gallons per minute. Test results showed that the CASS met each requirement and that an ACV intake system incorporating both the intake shroud and the CASS should protect the gas turbine engine from saltwater ingestion.

A Centrifugal Compressor Impeller: A Multidisciplinary Optimization to Improve its Mass, Strength, and Gas-Dynamic Characteristics

2017 ◽  
Author(s):  
Anton Salnikov ◽  
Maxim Danilov
Keyword(s):  
Gas Turbine ◽  
Centrifugal Compressor ◽  
Problem Formulation ◽  
Gas Turbine Engine ◽  
Multidisciplinary Optimization ◽  
Design Quality ◽  
Compressor Wheel ◽  
Turbine Engine ◽  
Development Costs ◽  
Compressor Impeller

The high-loaded centrifugal compressor blisk-type impeller, one of the main low-sized gas-turbine engine components, strongly affects engine efficiency. However, its design is a time-consuming and complex task for several reasons, including its high loading, the large number of structural and technological constraints, and the variety of requirements needed for application to a gas-turbine engine centrifugal compressor impeller (e.g., increased efficiency and strength, minimized weight requirements, etc.). The imposition of several constraints for structure modification of the centrifugal wheels can improve one characteristic but can worsen others. The standard solution for this problem is to use an iterative approach, whereby the design process is reduced to a consistent set of impeller element design problem statements and decisions; these are separate for different analysis disciplines. The main drawbacks to this approach are that it is labor intensive and can cause deterioration of the design quality because this procedure does not consider the design object as a unit. The present work considers a centrifugal compressor wheel design approach based on the use of an integrated multidisciplinary parameterized 3D model. This model includes a number of specialized sub-models that describe the necessary design areas as well as physical process features and phenomena occurring in the designed object. The model also realizes the integration and interaction of sub-models used in an integrated computing space. The proposed approach allows the optimization of the structure based on several criteria, such as the mass of the wheel, stage efficiency, strength, economic indicators, etc. The result of multi-criteria optimization is not a single product design, but a set of optimal Pareto points, which describes a number of centrifugal wheel models. The optimal configuration is selected from this set, based on what is considered the most important criterion. Optimization criteria may vary depending on the problem formulation, but the design technology, parameterization scheme, and choice of multidisciplinary integrated mathematical model are retained. Therefore, in the case of a product requirement correction, a new optimal design will require less time. In aggregate, with the nonlinear constrained optimization application, this approach reduces the total time of the design cycle, decreases development costs, and improves quality.

scholarly journals Application of the vacuum casting technology in the production of small-size gas turbine engine blade machines

2021 ◽  
Vol 20 (3) ◽  
pp. 152-159
Author(s):  
A. M. Faramazyan ◽  
S. S. Remchukov ◽  
I. V. Demidyuk
Keyword(s):  
Gas Turbine ◽  
Centrifugal Compressor ◽  
Gas Turbine Engine ◽  
Shrinkage Porosity ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Vacuum Casting ◽  
Turbine Engine ◽  
Design Values ◽  
The Cost

The application of casting technologies in the production of parts and assemblies of small-size gas turbine engines is justified in the paper. The technology of vacuum casting in gypsum molds was tested during the production of an experimental centrifugal compressor of a small-size gas turbine engine. On the basis of a 3D model of the designed centrifugal compressor, computational studies of vacuum casting were carried out and rational parameters of the technological process were determined. Prototypes of the developed centrifugal compressor of a small-size gas turbine engine were made. The results of calculations and the performed technological experiment confirmed the fill rate of the gating form and the absence of short pour. The distribution of shrinkage porosity and cavities corresponds to the design values and is concentrated in the central part of the casting that is subjected to subsequent machining. The area of the blades, disc and sleeve is formed without defects. The use of casting technologies in the production of parts and assemblies of small-size gas turbine engines assures the required quality with a comparatively low price of the finished product, making it possible to achieve the balance between the cost of the technology and the quality of the product made according to this technology.

scholarly journals Creating a multi-level model of a centrifugal compressor for a digital analogue of the gas turbine engine

2019 ◽  
Vol 604 ◽  
pp. 012050
Author(s):  
Evgenii Marchukov ◽  
Igor Egorov ◽  
Grigorii Popov ◽  
Oleg Baturin ◽  
Andrei Volkov ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Centrifugal Compressor ◽  
Gas Turbine Engine ◽  
Turbine Engine ◽  
Level Model ◽  
Multi Level

Development of a Centrifugal Compressor for a Small Gas-Turbine Engine

1956 ◽  
Author(s):  
N. R. Balling ◽  
V. W. van Ornum
Keyword(s):  
Research And Development ◽  
Gas Turbine ◽  
Fuel Consumption ◽  
Centrifugal Compressor ◽  
Pressure Ratio ◽  
Development Program ◽  
Gas Turbine Engine ◽  
Specific Fuel Consumption ◽  
General Description ◽  
Turbine Engine

The objective of the research and development program reported by this paper was to decrease the specific fuel consumption of a small gas-turbine engine by means of an increase in pressure ratio alone. Development of a centrifugal compressor is presented, with a general description of equipment, methods, and special problems met during the tests. Results showed the required decrease in specific fuel consumption and pointed up the advantages of a straightforward development program.

scholarly journals Experience in using anisotropic properties of composites in engineering the compressor impeller of a small-size gas turbine engine

2020 ◽  
Vol 329 ◽  
pp. 03029
Author(s):  
L. A. Martynyuk ◽  
L. V. Bykov ◽  
A. D. Ezhov ◽  
P. I. Talalaeva ◽  
D. V. Afanasiev
Keyword(s):  
Composite Materials ◽  
Gas Turbine ◽  
Centrifugal Compressor ◽  
High Strength ◽  
Gas Turbine Engine ◽  
Rocket Engines ◽  
Turbine Engine ◽  
Anisotropy Of Properties ◽  
Reinforcing Fibers ◽  
Compressor Impeller

The use of composite materials in modern aircraft and rocket engines is one of the most promising areas. Low density and high strength characteristics of composite materials are crucial when choosing a material for small-sized compressors. The main ability to bear the load of the composite material is provided by the reinforcing fibers of the filler. The greater the percentage of filler fibers has a particular orientation, the higher the strength and rigidity of the product in this direction. If the part is loaded with forces applied primarily in one or two directions, it makes sense to create a material with anisotropy of properties that will exactly match the applied loads. For example, the disk and blades of a centrifugal compressor operate under the action of centrifugal force and gas pressure. In this case, to manufacture a centrifugal compressor impeller from composite materials, it is only necessary to redistribute the fibers in the part space in such a way as to create an optimal anisotropy of properties. This article describes the procedure for selecting the optimal orientation of reinforcing fibers in the impeller of a centrifugal compressor of a small gas turbine engine.

Disc-Type Airborne Vehicle and Radial Flow Gas Turbine Engine Used Therein

2001 ◽  
Author(s):  
Norman L. Heuvel
Keyword(s):  
Gas Turbine ◽  
High Speed ◽  
Radial Flow ◽  
Turbine Blades ◽  
Gas Turbine Engine ◽  
Compressor Blades ◽  
Turbine Engine ◽  
Air Inlet ◽  
Airborne Vehicle ◽  
Engine Rotors

An annular, radial flow gas turbine engine and airborne vehicle utilizing same for jet propulsion. The engine comprises counter-rotating rotors and a compressor section with counter-rotating annular rows of intermeshing compressor blades, an annular combustion section common to both rotors wherein the combustion zone is defined by oppositely rotating rotor walls, and a turbine section made up of annular rows of counter-rotating exhaust turbine blades. No stator blades are present in either the compressor or the turbine sections. The craft comprises a central hub on which the engine rotors rotate on thrust bearings, and speed-staged bearings maintain rotor tolerances with respect to each other and to nonrotating shell portions above and below the engine rotors. Air inlet guide vanes leading to the compressor section are also housed in the hub portion of the craft. Exhaust gases emitting from the turbine section are selectively ducted through the annularly arranged-downwardly directed lift thrust producing ducts and/ or rearwardly directed ducts or vanes for generation of forward propulsion. Directional control during hovering and low speed flight is by selective braking of one or the other of the rotors. and during high speed flight also by selective control of spoiler surfaces arranged in the upper and lower external surfaces of the craft.

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