Ishikawajima-Harima Heavy Industries Research Articles

A magnetostriction device (applied to electromechanical filters and strain gauges)

The Institute of Space and Astronautical Science (ISAS) has been engaged in the development study on the Air Turbo Ramjet (ATR) engine since 1986 in cooperation with the Ishikawajima Harima Heavy Industries Co. Ltd (IHI). The ATR is one of the most preferable candidates for the propulsion system of a future space plane. Our ATR engine is a combined cycle air breathing propulsion system which consists of the turbojet and the fan boosted ramjet using the liquid hydrogen as a fuel. This engine system was named “ATREX” after employing the expander cycle. The ATREX is energized by thermal energy extracted regeneratively in both the pre-cooler installed in the air intake and the heat exchanger in combustion chamber. The ATREX works in the flight condition from sea level static up to Mach 6 at 35 km altitude. The ATREX employs the tip turbine configuration for compactness of turbo machinery. We are assessing the feasibility of the ATREX system by the sea level static tests using the 14-scale model (ATREX-500) with a fan inlet diameter of 300 mm and overall length of 2120 mm. In 1990, the ATREX-500 engine was tested in a sea level static condition to verify the performance characteristics of the turbo machinery and the combustor. In September of 1991, the heat exchanger was installed in the combustion chamber and tested independently from the turbo system. In November of 1991, the heat exchanger was coupled with the turbo system and tested to verify the overall system of the ATREX. In this paper are presented the test results of the ATREX-500 engine tested in the sea level static condition.

Supersonic wave converter

The Institute of Space and Astronautical Science (ISAS) has been engaged in the development study on the Air Turbo Ramjet (ATR) engine since 1986 in cooperation with the Ishikawajima Harima Heavy Industries Co. Ltd (IHI). The ATR is one of the most preferable candidates for the propulsion system of a future space plane. Our ATR engine is a combined cycle air breathing propulsion system which consists of the turbojet and the fan boosted ramjet using the liquid hydrogen as a fuel. This engine system was named “ATREX” after employing the expander cycle. The ATREX is energized by thermal energy extracted regeneratively in both the pre-cooler installed in the air intake and the heat exchanger in combustion chamber. The ATREX works in the flight condition from sea level static up to Mach 6 at 35 km altitude. The ATREX employs the tip turbine configuration for compactness of turbo machinery. We are assessing the feasibility of the ATREX system by the sea level static tests using the 14-scale model (ATREX-500) with a fan inlet diameter of 300 mm and overall length of 2120 mm. In 1990, the ATREX-500 engine was tested in a sea level static condition to verify the performance characteristics of the turbo machinery and the combustor. In September of 1991, the heat exchanger was installed in the combustion chamber and tested independently from the turbo system. In November of 1991, the heat exchanger was coupled with the turbo system and tested to verify the overall system of the ATREX. In this paper are presented the test results of the ATREX-500 engine tested in the sea level static condition.

Ultrasonic technique for determining sound-velocity change in high-loss materials: Asay, R., Lamberson, L., Guenther, H., JASA, vol 45, no 3 (March 1969) pp 566–571

The Institute of Space and Astronautical Science (ISAS) has been engaged in the development study on the Air Turbo Ramjet (ATR) engine since 1986 in cooperation with the Ishikawajima Harima Heavy Industries Co. Ltd (IHI). The ATR is one of the most preferable candidates for the propulsion system of a future space plane. Our ATR engine is a combined cycle air breathing propulsion system which consists of the turbojet and the fan boosted ramjet using the liquid hydrogen as a fuel. This engine system was named “ATREX” after employing the expander cycle. The ATREX is energized by thermal energy extracted regeneratively in both the pre-cooler installed in the air intake and the heat exchanger in combustion chamber. The ATREX works in the flight condition from sea level static up to Mach 6 at 35 km altitude. The ATREX employs the tip turbine configuration for compactness of turbo machinery. We are assessing the feasibility of the ATREX system by the sea level static tests using the 14-scale model (ATREX-500) with a fan inlet diameter of 300 mm and overall length of 2120 mm. In 1990, the ATREX-500 engine was tested in a sea level static condition to verify the performance characteristics of the turbo machinery and the combustor. In September of 1991, the heat exchanger was installed in the combustion chamber and tested independently from the turbo system. In November of 1991, the heat exchanger was coupled with the turbo system and tested to verify the overall system of the ATREX. In this paper are presented the test results of the ATREX-500 engine tested in the sea level static condition.

The effect of ultrasound on the dislocation structure of molybdenum single crystals (tests at 5, 10 and 30MHz and 150 Watts/cm2)

The Institute of Space and Astronautical Science (ISAS) has been engaged in the development study on the Air Turbo Ramjet (ATR) engine since 1986 in cooperation with the Ishikawajima Harima Heavy Industries Co. Ltd (IHI). The ATR is one of the most preferable candidates for the propulsion system of a future space plane. Our ATR engine is a combined cycle air breathing propulsion system which consists of the turbojet and the fan boosted ramjet using the liquid hydrogen as a fuel. This engine system was named “ATREX” after employing the expander cycle. The ATREX is energized by thermal energy extracted regeneratively in both the pre-cooler installed in the air intake and the heat exchanger in combustion chamber. The ATREX works in the flight condition from sea level static up to Mach 6 at 35 km altitude. The ATREX employs the tip turbine configuration for compactness of turbo machinery. We are assessing the feasibility of the ATREX system by the sea level static tests using the 14-scale model (ATREX-500) with a fan inlet diameter of 300 mm and overall length of 2120 mm. In 1990, the ATREX-500 engine was tested in a sea level static condition to verify the performance characteristics of the turbo machinery and the combustor. In September of 1991, the heat exchanger was installed in the combustion chamber and tested independently from the turbo system. In November of 1991, the heat exchanger was coupled with the turbo system and tested to verify the overall system of the ATREX. In this paper are presented the test results of the ATREX-500 engine tested in the sea level static condition.

Simulated hydrophone response

The Institute of Space and Astronautical Science (ISAS) has been engaged in the development study on the Air Turbo Ramjet (ATR) engine since 1986 in cooperation with the Ishikawajima Harima Heavy Industries Co. Ltd (IHI). The ATR is one of the most preferable candidates for the propulsion system of a future space plane. Our ATR engine is a combined cycle air breathing propulsion system which consists of the turbojet and the fan boosted ramjet using the liquid hydrogen as a fuel. This engine system was named “ATREX” after employing the expander cycle. The ATREX is energized by thermal energy extracted regeneratively in both the pre-cooler installed in the air intake and the heat exchanger in combustion chamber. The ATREX works in the flight condition from sea level static up to Mach 6 at 35 km altitude. The ATREX employs the tip turbine configuration for compactness of turbo machinery. We are assessing the feasibility of the ATREX system by the sea level static tests using the 14-scale model (ATREX-500) with a fan inlet diameter of 300 mm and overall length of 2120 mm. In 1990, the ATREX-500 engine was tested in a sea level static condition to verify the performance characteristics of the turbo machinery and the combustor. In September of 1991, the heat exchanger was installed in the combustion chamber and tested independently from the turbo system. In November of 1991, the heat exchanger was coupled with the turbo system and tested to verify the overall system of the ATREX. In this paper are presented the test results of the ATREX-500 engine tested in the sea level static condition.

Observation of doppler-shifted acoustic cyclotron resonance: Voges, E., electronics letters (18 September 1969) (1834)

The Institute of Space and Astronautical Science (ISAS) has been engaged in the development study on the Air Turbo Ramjet (ATR) engine since 1986 in cooperation with the Ishikawajima Harima Heavy Industries Co. Ltd (IHI). The ATR is one of the most preferable candidates for the propulsion system of a future space plane. Our ATR engine is a combined cycle air breathing propulsion system which consists of the turbojet and the fan boosted ramjet using the liquid hydrogen as a fuel. This engine system was named “ATREX” after employing the expander cycle. The ATREX is energized by thermal energy extracted regeneratively in both the pre-cooler installed in the air intake and the heat exchanger in combustion chamber. The ATREX works in the flight condition from sea level static up to Mach 6 at 35 km altitude. The ATREX employs the tip turbine configuration for compactness of turbo machinery. We are assessing the feasibility of the ATREX system by the sea level static tests using the 14-scale model (ATREX-500) with a fan inlet diameter of 300 mm and overall length of 2120 mm. In 1990, the ATREX-500 engine was tested in a sea level static condition to verify the performance characteristics of the turbo machinery and the combustor. In September of 1991, the heat exchanger was installed in the combustion chamber and tested independently from the turbo system. In November of 1991, the heat exchanger was coupled with the turbo system and tested to verify the overall system of the ATREX. In this paper are presented the test results of the ATREX-500 engine tested in the sea level static condition.

Vibration analyser for on-the-spot measurements

The Institute of Space and Astronautical Science (ISAS) has been engaged in the development study on the Air Turbo Ramjet (ATR) engine since 1986 in cooperation with the Ishikawajima Harima Heavy Industries Co. Ltd (IHI). The ATR is one of the most preferable candidates for the propulsion system of a future space plane. Our ATR engine is a combined cycle air breathing propulsion system which consists of the turbojet and the fan boosted ramjet using the liquid hydrogen as a fuel. This engine system was named “ATREX” after employing the expander cycle. The ATREX is energized by thermal energy extracted regeneratively in both the pre-cooler installed in the air intake and the heat exchanger in combustion chamber. The ATREX works in the flight condition from sea level static up to Mach 6 at 35 km altitude. The ATREX employs the tip turbine configuration for compactness of turbo machinery. We are assessing the feasibility of the ATREX system by the sea level static tests using the 14-scale model (ATREX-500) with a fan inlet diameter of 300 mm and overall length of 2120 mm. In 1990, the ATREX-500 engine was tested in a sea level static condition to verify the performance characteristics of the turbo machinery and the combustor. In September of 1991, the heat exchanger was installed in the combustion chamber and tested independently from the turbo system. In November of 1991, the heat exchanger was coupled with the turbo system and tested to verify the overall system of the ATREX. In this paper are presented the test results of the ATREX-500 engine tested in the sea level static condition.

Supersonic delay path (steel bar with non-homogeneous zone)

The Institute of Space and Astronautical Science (ISAS) has been engaged in the development study on the Air Turbo Ramjet (ATR) engine since 1986 in cooperation with the Ishikawajima Harima Heavy Industries Co. Ltd (IHI). The ATR is one of the most preferable candidates for the propulsion system of a future space plane. Our ATR engine is a combined cycle air breathing propulsion system which consists of the turbojet and the fan boosted ramjet using the liquid hydrogen as a fuel. This engine system was named “ATREX” after employing the expander cycle. The ATREX is energized by thermal energy extracted regeneratively in both the pre-cooler installed in the air intake and the heat exchanger in combustion chamber. The ATREX works in the flight condition from sea level static up to Mach 6 at 35 km altitude. The ATREX employs the tip turbine configuration for compactness of turbo machinery. We are assessing the feasibility of the ATREX system by the sea level static tests using the 14-scale model (ATREX-500) with a fan inlet diameter of 300 mm and overall length of 2120 mm. In 1990, the ATREX-500 engine was tested in a sea level static condition to verify the performance characteristics of the turbo machinery and the combustor. In September of 1991, the heat exchanger was installed in the combustion chamber and tested independently from the turbo system. In November of 1991, the heat exchanger was coupled with the turbo system and tested to verify the overall system of the ATREX. In this paper are presented the test results of the ATREX-500 engine tested in the sea level static condition.

100 kg/mm<SUP>2</SUP>級高張力鋼溶接材の機械試験

A new ultra-high-strength steel of 100 kg/mm2 was developed jointly by the Ishikawajima-Harima Heavy Industries Co., Ltd. and the Yawata Iron and Steel Co., Ltd. Prior to use for structures and pressure vesseles, various weldability tests were undertaken. It has been established that the mechanical properties of the HT-100 steel weld-joint was satisfactory excepting H.A.Z. deterioration, and it is quite comparable to that of commercial heat treated 80 kg/mm2 high-strength steels. Many investigators, have pointed out that there exists a remarkable brittle zone in the weld-heat-affected zone of the heat-treated high tension steel, and such a brittle zone causes deterioration of weld-joint properties. The following conclusions were obtained as the result of investigation.(1) Brittleness of HT-100 steel was observed in the results of pressed-notch charpy, notched slow bend, drop weight and weld-joint wide tension tests.(2) When weld defects such as under-cut and angular distortion exist tensile strength decreases to below the yield point of HT-100 steel in the weld-joint wide tension tests.(3) Successful results in improving for over-all weldment properties were obtained by deposition of a protective weld bead called A.C.I. bead in this investigation. These effects were believed to be due to micro-structure refining, removing of stress consentration at weld toes, and increasing of thickness in the weld-heat-affected zone.

On the IHI Ship Model Basin

A new ship model basin of Ishikawajima-Harima Heavy Industries Co., Ltd. was established at Yokohama in January 1966. It consists of a towing tank (100m×10m×5m+10m×2m×1.5m), model manufacturing shops and laboratories.The towing carriage is made of steel box girders and its maximum speed is 5m/sec.The remarkable features of this model basin are as follows : (1) The Thyrister Leonard System is adopted to the speed regulation of the towing carriage. Then the sufficient steadiness and setting accuracy of the speed of the carriage are preserved.(2) The application of sequence program with punched cards made possible to simplify the measuring work and only one or two persons are needed for the ordinary experiments.(3) In the self-propulsion tests, the rate of propeller rotation is automatically corrected according to the relative speed between the carriage and the model. By this method the self-propelled model settles into a steady speed in a comparatively short time, therefore in spite of short length of the tank, sufficiently reliable data are obtained.(4) All experimental data in ordinary tests are detected directly by digital transducer.(5) The special detecting mechanism is used for the thrust measurements, which needs no slide coupling and the small displacement of the propeller shaft is converted to the phase difference between a couple of pulses.

On the High Speed Impact Tensile Test of Tough Steel-IN Steel

This paper describes the tensile impact properties of IN Steel which have been lately developed by the Ishikawajima-Harima Heavy Industries Co., Ltd., By using a high speed impact tensile testing machine with a large rotary disk installed at Tokyo Institute of Technology, the authors have obtained some results from the experiment.The impact velocity was varied from static region to 80m/s, and the test was performed at room temperature.The results obtained are summarized as follows:[1] Test results of the plain test pieces;(1) The impact tensile strength of IN Steel increased up to the impact velocity of 5m's and thereafter it was almost constant regardless of the impact velocity.(2) The maximum value of impact energy per unit volume of plain test pieces (d=8mm, l/d=5) was about 40kg·m/cm3 at the impact velocity of 40m/s.(3) The observed critical impact velocity was about 50m/s regardless of the gauge length of test pieces.(4) The contraction percentage of area decreased a little at the impact velocity of 5m/s, and thereafter it was not affected much by the value of impact velocity. It was about 80 percent.[2] Test results of the notched test pieces;(1) The impact tensile strength of notched test pieces was 60% larger than that of the plain test pieces and it was kept unchanged in the test until 20m/s of the impact velocity, but increased remarkably from that velocity up to 80m/s.(2) As the radii of curvature at the root of the notch is smaller, the impact tensile strength somewhat increased, but the value of impact energy per unit area was kept unchanged.(3) If the diameter of notched test pieces and radii of curvature were constant, the impact tensile strength and the value of impact energy per unit area were kept unchanged, even if the outer diameter varied D/d=1.75, 1.875 and 2.125.(4) On the effect of the size of notched test pieces, having similar shapes, the smaller ones in size had larger impact tensile strength, but the value of impact energy per unit area showed a reversal tendency.Generally speaking, it may be concluded that IN Steel provides excellent mechanical properties against high speed impact loading.

Technical information activities of Ishikawajima-Harima Heavy Industries Co.

Technical information activities of Ishikawajima-Harima Heavy Industries Co.

On the 13000kg/hr Supercritical Pressure Test Boiler

This paper presents the features of a 13000kg/hr supercritical test boiler which was erected at the third factory of the Ishikawajima-Harima Heavy Industries Company and also describes the experimental results of its steady and dynamic test. Especially the analysis of dynamic test is made in comparison with the simulation by the analogue computer. Test results can be applied to development of the central supercritical pressure steam generator.

Medical Management of Hypertensives in Ishikawajima Harima Heavy Industries

Medical Management of Hypertensives in Ishikawajima Harima Heavy Industries