Measurements of pressure in front of shock wave : assessment of methodology influence on the measurement results on the basis of experiments with the shock tube

• Autorzy: Perkowski W. , Irzycki A. , Kawalec M. , Łukasik B. , Snopkiewicz K.
• Języki publikacji: EN

Abstrakty

EN

The experiments, described in the article, are related to research of a rotating detonation that has been conducted in the Institute of Aviation in Warsaw since 2009, under the OPIE project: “Turbine engine with detonation combustion chamber”. Measurements of the shock wave parameters, are among the most difficult in the art. This is due to high speed of the wave transition, and above all, a very small thickness of the shock wave. For the purposes of the mentioned project, a methodology for measuring pressure on the rotating detonation wave was developed. It included the type of sensors, their location and their protection from heat and flames. In order to determine the capabilities, limitations and accuracy of the method that was used, a series of experiments were planned and carried out. They enabled the assessment of the impact, on the measurement of pressure in the shock wave, of the following factors: the location of the sensor (frontal and lateral) relative to the shock wave front, protrusion or retraction of the sensor in its housing, the covering of the sensor with a protective layer (such as a high temperature silicon). This paper presents the results of the experiments that were carried out with use of a small shock tube of a simple design. The high-pressure part of the tube (so-called “driver”) was charged with the compressed nitrogen gas. The membrane was designed to be torn by pressure and pressure magnitude of the shock wave were measured by a “twin pair” of the Kistler 603B type piezoelectric sensors, one of which was always the reference sensor.

Słowa kluczowe

EN

shock wave; shock tube; pressure measurements

• Wydawca: Łukasiewicz Research Network - Institute of Aviation ; European Science Society of Powertrain and Transport KONES Poland ; Wydawnictwo Instytutu Technicznego Wojsk Lotniczych
• Czasopismo: Journal of KONES
• Rocznik: 2013
• Tom: Vol. 20, No. 4
• Strony: 333--340
• Opis fizyczny: Bibliogr. 6 poz., rys.

Twórcy

autor

Perkowski W.

• Institute of Aviation Krakowska Av. 110/114, 02-256 Warsaw, Poland tel.: [phone] ext. 426, fax: [phone]

autor

Irzycki A.

• Institute of Aviation Krakowska Av. 110/114, 02-256 Warsaw, Poland tel.: [phone] ext. 426, fax: [phone]

autor

Kawalec M.

• Institute of Aviation Krakowska Av. 110/114, 02-256 Warsaw, Poland tel.: [phone] ext. 426, fax: [phone]

autor

Łukasik B.

• Institute of Aviation Krakowska Av. 110/114, 02-256 Warsaw, Poland tel.: [phone] ext. 426, fax: [phone]

autor

Snopkiewicz K.

• Institute of Aviation Krakowska Av. 110/114, 02-256 Warsaw, Poland tel.: [phone] ext. 426, fax: [phone]

Bibliografia

• [1] Curchack, H. D., Davis, H. J., Shock Tube Techniques and Instrumentation, Harry Diamond Laboratories, Report TR-1429, March 1969.
• [2] Glass, I. I., Shock Waves & Man, University of Toronto Institute for Aerospace Studies, 1974.
• [3] Jagadeesh, G., Fascinating World of Shock Waves, Resonance, August 2008.
• [4] McGraw-Hill, Encyclopaedia of Science and Technology, McGraw-Hill Companies, Inc.
• [5] McGraw-Hill, Dictionary of Aviation, McGraw-Hill Companies, Inc.
• [6] Walter, P. L., Air-Blast and the Science of Dynamic Pressure Measurements, Sound and Vibration, December 2004.