Session: 13-11 Advanced Methods (II)

Paper Number: 122051

122051 - Configuration of a Heat Transfer Design Verification Test System Using Airfoil Additive Manufacturing 

In the process of designing novel high-pressure turbine components, temperature emerges as a pivotal factor, given its profound impact on material stress thresholds and operational life. Hence, it is imperative not only to derive efficient cooling designs but also to establish methods for their effective and reliable validation.

In particular, prior to the installation of engine components such as turbine blades and vanes, extensive research efforts have been directed towards conducting rig tests to acquire surface temperature data for the validation of heat transfer designs. While temperature measurements have historically been performed using various methods such as infrared, thermocouples, and thermal paints, ongoing research are actively addressing challenges associated with factors like emissivity, radiative properties, transmissivity, flow interference, and data resolution.

In addition, it's typical for airfoil-shaped components used in the military aircraft engines to have circumferential lengths of just a few tens of millimeters. Attaching thermocouples to the surface can disrupt external airflow and lead to sensor detachment due to the high-speed air movement, underscoring the demand for innovative approaches.

In this study, we employed an additive manufacturing(AM) method to fabricate turbine blades and vane specimens that closely resemble the shape of actual components, intended for surface temperature measurements. Additionally, we established a high-temperature test rig equipped with three types of pyrometers for simultaneous acquisition of cooling airfoils surface temperature data.

For the AM test specimens, we built channels in both the pressure and suction sides, allowing for the insertion of thermocouples with a 0.8mm diameter from the cooling air supply to the airfoil surface. For the test rig, we configured an angular-shaped flow path to accommodate multiple cooling airfoil specimens, and established a bypass system capable of supplying high-temperature gas at a flow rate of 1.5 kg/s by combusting liquid fuel.

Through these experiments, we were able to compare errors based on measurement methods and obtain data for selecting sensors suitable for observations under different test conditions.

Presenting Author: Keekeun Kim Agency for Defense Development

Presenting Author Biography: (2021) Ph. D in Mechanical Engineering
(~Present) Senior Researcher in Agency for Defense Development(ADD)
Aerospace Technology Research Institute 3rd Directorate

Authors:

Keekeun Kim Agency for Defense Development
Junwon Suh Agency for Defense Development
Dongwha Kim Agency for Defense Development
Youngmin Kwon Agency for Defense Development
Kwanho Moon Agency for Defense Development
Gyongwon Ryu Agency for Defense Development