Influence of Labyrinth Seal Leakage on the Turbine Support Cooling

Виноградов, А. С.; Badykov, Renat R.

doi:10.1115/gtindia2014-8172

Cited by 5 publications

(2 citation statements)

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“…Engines with advanced parameters require seals operating for a long time with low leakages [1][2][3][4][5]. The basic type of seals applied for gas turbine engine rotor supports is face seal.…”

Section: Introductionmentioning

confidence: 99%

Development of Advanced Carbon Face Seals for Aircraft Engines

Фалалеев

Бондарчук

Tisarev

2018

IOP Conf. Ser.: Mater. Sci. Eng.

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Abstract. Abstract. Modern aircraft gas turbine engines require the development of seals which can operate for a long time with low leakages. The basic type of seals applied for gas turbine engine rotor supports is face seal. To meet the modern requirements of reliability, leak-tightness and weight, low-leakage gas-static and hydrodynamic seals have to be developed. Dry gas seals use both gas-static and hydrodynamic principles. In dry gas seals microgrooves are often used, which ensure the reverse injection of leakages in the sealed cavity. Authors have developed a calculation technique including the concept of coupled hydrodynamic, thermal and structural calculations. This technique allows to calculate the seal performance taking into account the forces of inertia, rupture of the lubricant layer and the real form of the gap. Authors have compared the efficiency of seals with different forms of microgrooves. Results of calculations show that seal with rectangular form of microgrooves has a little gap leading to both the contact of seal surfaces and the wear. Reversible microgrooves have a higher oil mass flow rate, whereas HST microgrooves have good performance, but they are difficult to produce. Spiral microgrooves have both an acceptable leakages and a high stiffness of liquid layer that is important in terms of ensuring of sealing performance at vibration conditions. Therefore, the spiral grooves were chosen for the developed seal. Based on calculation results, geometric dimensions were chosen to ensure the reliability of the seal operation by creating a guaranteed liquid film, which eliminates the wear of the sealing surfaces. Seals designed were tested both at the test rig and in the engine. IntroductionEngines with advanced parameters require seals operating for a long time with low leakages [1][2][3][4][5]. The basic type of seals applied for gas turbine engine rotor supports is face seal. To meet the modern requirements of reliability, leak-tightness and weight, low-leakage gas-static and hydrodynamic seals have to be developed [6,7]. Dry gas seals use both gas-static and hydrodynamic principles. In dry gas seals microgrooves are often used, which ensure the reverse injection of leakages in the sealed cavity.The operating principle of such type of seals is based on the balance of axial forces, acting on axiallymovable and rotating rings. Complex-shaped microgrooves are produced on the face area [1][2]. At operational conditions pressure rises up in the gap that leads to the displacement of axial-movable ring and minimum positive clearance of 1…3 μm in friction couple is formed. It allows seal to operate with low leakages without the wear for the wide range of operating parameters.Application of modern materials, complex-shaped microstructures and improvement in manufacturing technology allow to broaden their functional possibilities. Therefore, authors have decided to apply the low leakage seals technology in order to improve existing face seals and to develop advanced face seal constructions applied for...

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Section: Introductionmentioning

confidence: 99%

Development of Advanced Carbon Face Seals for Aircraft Engines

Фалалеев

Бондарчук

Tisarev

2018

IOP Conf. Ser.: Mater. Sci. Eng.

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“…PHYS. 13, 01010 (2021) 01010-5 tural elements of the engine, the volume and mass of the elements that are part of the node, and then the nodes and the engine as a whole [8,10] were calculated:…”

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confidence: 99%

Behavior of the Aviation Engine Control System During the Transition to the Lorenz Attractor

Tovkach¹

2021

J. Nano- Electron. Phys.

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The article considers the Lorentz attractor in aviation engine control systems (AECS) to obtain the necessary characteristics of the starting system and the laws of fuel supply, and to determine the emission characteristics. The defined behavior of the control system allows to optimize the control program of adjustable elements of the flowing part of the gas generator in transition modes of operation; to get a full picture of the starting characteristics of the developed engine, including reserves of gas-dynamic stability (GDS) in the starting modes; to establish the necessary programs for regulating the guide devices (GD), air bypass from the compressor; to select the required starter power, start-up cycle and fuel supply program in ground, alpine and flight conditions at the expected temperatures of air, fuel and oil in operation. Euler's and Runge-Kutta methods, Lorentz attractor are considered as the main approaches to mathematical modeling of AECS. The script of the interface of the modeling program includes the possibility of two-level modeling of the flowing part with the properties of end-to-end automated calculation: input of initial data and calculation of thermodynamic parameters of the engine; design of the flowing part of the engine based on the node approach; strength design and mass analysis; export data to files for CAD systems for further processing and interpretation.

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Advanced Dynamic Model Development of Dry Gas Seal

Badykov

Фалалеев

2017

Procedia Engineering

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Influence of Labyrinth Seal Leakage on the Turbine Support Cooling

Cited by 5 publications

References 0 publications

Development of Advanced Carbon Face Seals for Aircraft Engines

Development of Advanced Carbon Face Seals for Aircraft Engines

Behavior of the Aviation Engine Control System During the Transition to the Lorenz Attractor

Advanced Dynamic Model Development of Dry Gas Seal

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