H2POWRD – Harnessing Hydrogen’s Potential with Rotating Detonation: Call for applications to 15[...]

Technichal University Berlin; Deutschland; Vor Ort; EUR 40.000 - 60.000; Vollzeit

Zusammenfassung

A leading academic institution in Germany is offering full-time PhD positions within the H2POWRD project. The role involves engaging in cutting-edge research focused on hydrogen-powered technologies and working closely with a consortium of prominent European institutions. Candidates should hold a Master’s degree in relevant engineering fields and have excellent English communication skills. The project offers competitive salaries and opportunities for extensive professional development.

Leistungen

Competitive salary

Access to state-of-the-art research

Participation in training and workshops

Qualifikationen

• Must have a Master's degree in Mechanical, Energy, Chemical Engineering, Physics, or equivalent.
• Candidates should have research experience in relevant fields.
• Excellent command of English is required.

Aufgaben

• Engage in innovative research activities in hydrogen power technology.
• Contribute to collaborative projects across multiple European institutions.
• Participate in training and workshops related to PhD programs.

Kenntnisse

Master’s degree in a relevant field

Research experience (1 - 4 years)

Excellent English proficiency

Ausbildung

Master Degree or equivalent in Mechanical, Energy, Chemical Engineering or closely related

Jobbeschreibung

Organisation/Company Technichal University Berlin Department Mechanical Engineering and Transport Research Field Engineering » Aerospace engineering Engineering » Mechanical engineering Engineering » Thermal engineering Researcher Profile First Stage Researcher (R1) Positions PhD Positions Country Germany Application Deadline 31 Dec 2025 - 22:00 (Europe/Berlin) Type of Contract Temporary Job Status Full-time Hours Per Week 40 Offer Starting Date 2 Mar 2025 Is the job funded through the EU Research Framework Programme? Horizon Europe - MSCA Marie Curie Grant Agreement Number 101169009 Is the Job related to staff position within a Research Infrastructure? No

Offer Description

The Project

H2POWRD is a MSCA Doctoral Network aimed at training 15 early-stage researchers to develop a set of innovative research activities in the field of hydrogen powered rotating detonation combustion integrated in gas turbines for possible future high efficiency power plants and aircraft engines.

H2POWRD has been built to provide doctoral training in a collaborative partnership between academic and industry partners. The aim of this partnership is thus to understand the physical processes inherent in the stabilization of the rotating detonation wave, the conditioning of the unsteady exhaust flow, and the interaction of the RDC exhaust with subsonic and supersonic turbines. The scientific program is organized across three interconnected work areas, namely: (1) the combustor, (2) the transition duct, and (3) the turbine. This research agenda aims to accelerate the development of this revolutionary technology and explore the most pressing challenges to its further adoption.

The project H2POWRD will recruit 15 Doctoral Candidates (DC) in thirteen prominent institutions spread across six countries in Europe (Germany, France, Italy, Sweden, Belgium, and the Netherlands). In addition, nine Associate Partners (including gas turbine and aeroengine industries) will support training and secondments for the DCs.

The Consortium

SAFRAN SA (SAFRAN) (FR)

Associated Partners

Trustees of Purdue University (UP)

AEDUS Space Ltd (AEDUS)

Nagoya University (NU)

GE AVIO SRL (AVIO)

University of Cincinnati (UC)

Application Process:

Please do not send your applications directly to the point-of-contact for each DC.

The mail subject must begin with [DCXX] where XX is the project number (e.g. DC01 or DC13). Please include a letter of interest, a CV and at least one recommendation letter as a single pdf file (max file size 5 MB).

Applicants should send separate emails for each position for which they would like to apply.

IMPORTANT NOTE: Some host institutions require additional submission of the application documents via the host’s submission system.

IMPORTANT NOTE 2: Please recognize that individual projects may have application deadlines and start dates that differ from the stated date at the top of the Euraxess posting. The DC-specific dates and deadlines are listed with each project below.

URGENT: Individual Projects (Open)

DC15

• Title: Thermo-economic optimization and hybridization strategies
• Objectives: The DC will collect input from all the partners in order to assess the cycle performance and thus the potential of PGC in open and Combined Cycle with the goals of identifying the most promising layout options considering also off‑design performance and the hybridization with fuel as storage option (H2/NH3/Biomethane) includinging also power to gas solutions. At System level: i) for Combined Cycle/ and mixed Gas/Steam Cycle, the investigation of close/open loop steam blade cooling solutions has the potential to further increase the performance in term of efficiency for system designed for continuous use, moreover off‑design analysis will be performed to evaluate the load following capability; ii) for Open Cycle, the adoption of the RDC based‑layout could lead to simplify the compressor design and with a potential of capital cost reduction for peak‑operation systems in land application or size and weight reduction for propulsion purposes. So a proper optimization of the thermo‑economic performance is required.

Deadline: december 17th 2025 at 12 noon (CET)

Individual Projects (Closed)

DC01

• Title: Experimental investigations of low total pressure loss injectors on wave stabilization and performance
• Supervisor: Myles Bohon
• Objectives: Previous results of the INSPIRE program have shown that the reactant injector plays a pivotal role in the operation of the RDC. The injector is responsible for the double tasks of rapidly injecting and mixing the reactants between successive wave passages while also resisting the backflow of reactants in high pressure region behind the detonation wave. When poorly designed, the reactants are poorly mixed which reduces the combustion efficiency, or the injectors are too weak and the detonation wave degrades into counterrotating waves. Previous injectors have overcome these challenges by simply allowing large pressure losses through the injector, however this comes at the cost of overall pressure gain. The current project will explore a range of injector configurations (e.g. axial jet-in-crossflow, co‑annular pintle, inner‑ and outer‑rearward step injector configurations) designed to minimize the total pressure loss while maximizing the mixing. The project will incorporate scale model tests using acetone PLIF, reactive tests in the RDC to investigate performance and wave stabilization, throttling and operating envelope, comparison with numerical simulations performed with DC04 and DC07, and Machine Learning techniques applied to the large data sets of high frequency experimental measurements to train ML algorithms for high‑fidelity interpretation of low‑resolution measurements.
• Application Deadline: Feb. 7, 2025 (Closed)
• Planned Start Date: April 1, 2025

DC02

• Title: Direct Numerical Simulation (DNS) of H2‑air detonation waves under RDC‑relevant conditions and development of reduced‑order theoretical model of RDC wave dynamics
• Objectives: The objective is to better understand the fundamental propagation mechanism of irregular‑cell (e.g., in an H2‑air mixture) detonation under two RDC‑relevant scenarios—propagation with (1) lateral expansion and (2) inhomogeneously mixed reactants. 2D and 3D DNS will be used to simulate H2‑air detonation in a finite‑thickness layer of premixed or injected non‑premixed reactants bounded by a layer of hot detonation products. The data and findings from the DNS information will be used to develop a theoretical, reduced‑order model to more efficiently estimate RDC wave dynamics and shared with partners in the Consortium to validate Large Eddy Simulations of H2‑air detonation.
• Application Deadline: Feb. 7, 2025 (Closed)
• Planned Start Date: April 1, 2025

DC03

• Title: Experimental investigation of RDCs for gas generator applications in rocket propulsion
• Supervisor: Dr. Justin Hardi
• Host Institution: German Aerospace Center (DLR); Institute of Space Propulsion
• Objectives: The goal of this project is to investigate if the conventional gas generator in a liquid propellant rocket propulsion system that drives the turbopumps in many European launcher engines could be replaced by a rotating detonation combustor (RDC). The main technical challenges and research questions that need to be addressed are whether a stable detonation can be achieved and sustained at very low propellant mixture ratios and how the flow and pressure dynamics of the rotating detonation waves influence the driving of supersonic turbines.
• Application Deadline: Feb. 7, 2025 (Closed)
• Planned Start Date: April 1, 2025

DC04

• Title: Numerical study of injection and mixing in an air‑breathing RDC
• Co‑supervisor: Dmitry Davidenko
• Objectives: The objective of the PhD study is to optimize the injector design for an RDC fed with gaseous hydrogen and air. An optimized injector must provide efficient mixing, while limiting total pressure losses. The available time to mix the reactants is on the order of 100 μs, depending on the number of waves and their propagation speed. Several injection principles and geometries (shape, size and orientation of the orifices) will be compared according to the mixing efficiency and total pressure recovery criteria. These criteria will be evaluated from simulation results using LES for the turbulent mixing in an RDC. The best configuration will be studied in more detail and further improved. Injector operation will be characterized in a cold‑flow continuous regime, then in a reactive reinjection regime in order to extend understanding of the injection and mixing processes occurring in a RDC. The optimized injector design will be tested on the experimental RDC of TUB in the scope of DC01. In parallel, first simulations of the operation of the TUB RDC will be set up to select the appropriate numerical methods and physical models. Post‑processing tools will be developed to analyse the mixture formation in the RDC. The experimental study by DC01 will make it possible to select an operating point of interest to be simulated by DC04. The numerical results of DC04 and the experimental results of DC01 can thus be compared. If necessary, the numerical approach will be tuned to achieve agreement with the detonation propagation speed and pressure signals in the experimental RDC. The final simulation results will provide detailed information about the mixture formation in the RDC and its interaction with propagating detonation waves. Additional mixing simulations of the optimized injector in the radial RDC configuration of DC14 will be performed.
• Application Deadline: March. 7, 2025 (Closed)
• Planned Start Date: April 1, 2025

DC05

• Title: Unsteady wall heat flux measurements under detonation conditions
• Objectives: Detonation is a combustion regime that allows for generating high pressure and high temperature burned gas. Due to short time and space scales, the detonation front propagates as in adiabatic thermal conditions. However, high temperature reached during this compressible combustion process induces high heat transfers to the wall, requiring the use of specific cooling systems in practical applications (steady conditions). Currently, wall heat flux is not well known and cannot be precisely predicted with standardly used formulations. Accurate databases need to be obtained from the simplest to the most representative conditions to master the wall heat flux in detonation combustion regime for practical application evaluation and control like in a RDE. This study will allow for determination of the effect of compressibility, of chemical reactions (CJ detonation) and dilution of fresh gas by residual burned gas (in RDE conditions) on heat transfers during the detonation front passing as well as during the burned gas period. The study will also try to correlate the detonation cell characteristics with the local unsteady heat flux.
• Contact person: Julien Sotton ([e-mail] ); Florent Virot ([e-mail] ). Reminder: do not send your application to the Contact Person, but see the "Application Process" section of this announcement.
• Application Deadline: April 1, 2025 (Closed)
• Planned Start Date: August 1, 2025

DC06

• Title: Interaction of the combustor and transition duct on RDC performance and unsteadiness
• Co‑supervisor: Myles Bohon
• Objectives: The objective of this project is to experimentally investigate the interaction of the RDC with the transition duct. This region is important for the preparation of the flow before entering the turbine. Therefore, the experimental aspects of this work will explore three main objectives: (i) develop and test a candidate film cooling liner in conjunction with DC09, test the integration of a transition duct in conjunction with the projects of WP4, and test an ejector geometry in conjunction with DC07 and DC08. The specific geometries will be decided in discussion with the relevant partners. The testing procedure common to these three objectives is to investigate the effect of the transition duct on the state of the gas at the end of the duct as well as to investigate the impact of the duct upstream on the detonation wave. The project will utilize high frequency pressure measurements, total pressure measurements, direct imaging, and PIV and schlieren imaging where appropriate to quantify the reduction in fluctuation intensity through this region while also considering the losses. In addition to exploring the flow field in the transition duct and the dependency of the interaction of this region on the detonation wave, the project will also provide experimental data for validation of the corresponding numerical studies.
• Contact person: Myles Bohon ([e-mail] ). Reminder: do not send your application to the Contact Person, but see the "Application Process" section of this announcement.
• Application Deadline: Feb. 7, 2025 (Closed)
• Planned Start Date: April 1, 2025

DC07

• Title: High fidelity LES of RDE combustion chamber coupled with ejector (RDE design optimization)
• Supervisor: Thierry Poinsot
• Objectives: The goal of this WP is to analyse, with Large Eddy Simulation, the complex coupling between an RDE chamber and an ejector. The complete system injector – Combustion chamber – Ejector will be simulated for the first time in a high‑fidelity fully coupled LES of RDE using the MISCOG technique (Wang et al 2014). This will allow a well‑posed efficiency analysis of an RDE design and a precise measure of the gap between the actual efficiency of RDEs and their theoretical idealized counterpart. The project will also focus on the impact of the ejector design on the effective efficiency of the RDE. These results will be of great fundamental and practical value for the RDE community.
• Contact person: Omar Dounia ([e-mail] ); Thierry Poinsot ([e-mail] ). Reminder: do not send your application to the Contact Person, but see the "Application Process" section of this announcement.
• Application Deadline: Feb. 7, 2025 (Closed)
• Planned Start Date: September 1, 2025

DC08

• Title: Theoretical and Numerical ejector modelling for subsonic turbine integration in rotating detonation combustor
• Co‑supervisor: Dr. Guillaume Fournier
• Objectives: A fundamental difficulty associated with turbomachinery integration in the rotating detonation combustor is the transonic, highly unsteady, high temperature, combustion exhaust gas that have a detrimental effect on turbine operability. A viable solution to mitigate theses effects consists of driving a subsonic turbine using a flow ejector. The flow mixes between the burned gases coming from the detonation chamber with the fresh air coming from the compressor. This will result in drastic reduction in flow speed, fluctuations and temperature. This option is retained in this project. The work will be an extension of preliminary numerical studies conducted in the previous research, that shed light to the relevance of using ejectors for turbine coupling.
• Application Deadline: April 30, 2025 (Closed)
• Planned Start Date: August 1, 2025

DC09

• Title: Numerical and experimental investigations of realistic cooling schemes in RDC
• Objectives: Cooling is one of the most predominant challenges to steady operation of RDC because of the high heat loads generated by the combustion process. Film cooling is one the most effective techniques to keep combustor wall at safe temperature levels. The objective of this research is to provide a first practical validation of film cooling process in an actual RDC. A baseline film cooling scheme will be applied at the RDC test rig installed at TUB, starting from numerical results achieved in the INSPIRE project. Measurements will provide validation data for high‑fidelity CFD modelling which will be carried out starting from the best practices developed at UNIFI based on AVBP code. The validated CFD modelling will then be used to explore possible optimization of film cooling process, by investigating different hole patterns and hole shaping at different levels of coolant mass flow. The film cooling process will not only be optimized in terms of thermal performance, but the additional air injected as coolant will also be analysed as deflagrative post‑detonation oxidizer to improve overall combustion efficiency. This effort will be supported by ML techniques for the development of a virtual chemistry mechanism capable of handling both regimes of detonation and deflagration combustion.
• Application Deadline: April 30, 2025 (Closed)
• Planned Start Date: July 1, 2025

DC10

• Title: Design optimization of high‑performance integrated transition duct and vanes for RDCs
• Objectives: The aim of the activity is the design of optimized high‑pressure vanes integrated in transition ducts to allow for the high performance coupling to rotating detonation combustors. In details, boundary conditions obtained from the test rigs analysed in H2POWRD will be used to design a subsonic vane, thus providing realistic design solutions to partners working experimentally on the turbine module. The subsonic solution will be designed in cooperation with VKI, who will analyse a subsonic vane. Target boundary conditions will be defined and used by POLITO to design the ducts and by the experimental partners to design the devices that will mimic the pulsating condition in the test rig. The design procedure aims at reducing fluctuations from the rotating detonation engine, at designing a vane mostly insensitive to the inlet angle fluctuations, and at obtaining the highest possible aerodynamic efficiency of the vane by weakening the losses associated to the unsteady development of secondary flow structures and shocks. As far as the latter are concerned, a solution based on end‑wall contouring and vane optimization will be initially designed. A flow control solution will hence be added by considering unsteady blowing of coolant that both energizes the boundary layer and shields the metal parts that are subject to high temperature levels. The subsonic solution without flow control will be manufactured and analysed by TUB in a dedicated campaign. A rotor row will be selected or designed for the duct/vane geometry to numerically evaluate stage performance.
• Application Deadline: March 31, 2025 (Closed)
• Planned Start Date: June 1, 2025
• Note: Applicants are directed to refer to the additional application requirements, particularly in terms of selection procedures based on local regulations and/or internationally recognized English language qualifications achieved. At the following link, more details in addition to the standard application procedure detailed below.

DC11

• Title: Experimental testing of a subsonic turbine cascade under pulsating inflow conditions
• Objectives: This project wants to investigate the role of the pulsating flow generated by Rotating Detonation Engine (RDE) combustors on the performance of a downstream subsonic turbine. The aerodynamics of a turbine vane exposed to combustor‑representative unsteady inflow conditions will be experimentally tested in a high‑speed cascade rig at von Karman Institute. The candidate will design and build an unsteady flow generator mimicking realistic RDC conditions upstream of the turbine, to be integrated upstream of the turbine cascade. The turbine flow will be measured by means of fast‑response aerodynamic probes, airfoil surface instrumentation and optical techniques (Schlieren, PIV). The aerodynamics and performance of the vane cascade will be investigated at different pulsating and steady inflow regimes to identify the effects of combustor‑turbine interactions. The experiments and complementary CFD simulations will be used to characterize the transient turbine aerodynamics. The ultimate objective of the doctoral project is to develop guidelines for the modeling and design of turbines for next‑generation rotating detonation engines. Secondments periods at three universities are planned.
• Planned Start Date: Feb. 1, 2025

DC12

• Title: Numerical investigation of a supersonic axial turbine cascade for cooling and efficiency enhancement under RDC conditions.
• Host Institution: KTH Royal Institute of Technology
• Objectives: The project aims to enhance the understanding of the non‑isothermal unsteady fluid flow downstream of the RDC interacting with the high‑pressure axial turbine stage and to develop optimal flow control blade cooling solutions within this context. Commonly, flow control strategies are used for enhancement of heat transfer in high‑pressure turbines (e.g., air film cooling). However, it is also common that these flow control strategies are applied to an already optimized turbine blade configuration. The proposed approach with this project is to integrate from the beginning into the optimization process the flow control technology to be used. Supersonic flow conditions associated with the high‑pressure axial turbine cascade are to be assessed. Unsteady high‑fidelity simulations based on Large Eddy Simulation approach are to be carried to understand the behavior of secondary flows and assessment of the high‑pressure turbine performance and heat transfer under relevant RDC operating conditions. Sensitivity to the operating and boundary conditions will be assessed (including impact of non‑isentropic temperature fluctuations).
• Contact person: Mihai Mihaescu ([e-mail] ). Reminder: do not send your application to the Contact Person, but see the "Application Process" section of this announcement.
• Planned Start Date: According to agreement

DC13

• Title: Design and experimental testing of a supersonic turbine cascade under unsteady conditions
• Objectives: The goal is to design and test a supersonic stage with an inlet Mach number in the range of 1.5-2. The design will consider a high unsteadiness in terms of magnitude and angles as typically expected at the inlet of the first stage; the design of the unsteadiness generator is also foreseen. A robust optimization will also be run for the stator and rotor; both will be tested in a cold linear blow‑down wind tunnel. Flow field will be qualified by pressure measurements and flow visualization. Unsteady CFD tuned to the test conditions will also be conducted to enhance the comprehension of experiments. Secondments at VKI, ENSMA, and KTH are foreseen.
• Contact person: Paolo Gaetani ([e-mail] ). Reminder: do not send your application to the Contact Person, but see the "Application Process" section of this announcement.

DC14

• Title: Radial RDC test rig coupled with a radial supersonic turbine
• Supervisor: Marc Bellenoue
• Objectives: The most studied RDGT configuration is the axial one, which is particularly relevant for high‑power systems. However, the specific configuration considering the coupling between a radial RDC with a radial turbine presents a great advantage in terms of compactness and could also offer an interesting potential gain of efficiency. This particular configuration will be studied here for the RDC alone and in coupling configuration with a radial turbine. Hence, a dedicated experimental setup will be installed allowing performance determination of such an integrated system. Hydrogen‑air configuration will be considered to represent air‑breathing applications. Pressure measurements and high‑speed visualization will be performed to characterize the detonation properties. The radial RDC will benefit from the injection technology developed at ONERA by DC04 to optimize the detonation process in such specific geometry. Moreover, set up will allow to consider the mixing aspects between burned gas flow exiting from the RDC and a cooling/co‑flow. This configuration will produce experimental reference data for the work carried out by SAFRAN (DC08) that considers ejector modelling for turbine integration. Finally, the set up will allow to identify the configuration that gives the best system efficiency.
• Application Deadline: April 1, 2025 (Closed)
• Planned Start Date: September 1, 2025

DC15

• Title: Thermo-economic optimization and hybridization strategies
• Objectives: The DC will collect input from all the partners in order to assess the cycle performance and thus the potential of PGC in open and Combined Cycle with the goals of identifying the most promising layout options considering also off‑design performance and the hybridization with fuel as storage option (H2/NH3/Biomethane) considering also power to gas solutions. At System level: i) for Combined Cycle/ and mixed Gas/Steam Cycle, the investigation of close/open loop steam blade cooling solutions has the potential to further increase the performance in term of efficiency for system designed for continuous use, moreover off‑design analysis will be performed to evaluate the load following capability; ii) for Open Cycle, the adoption of the RDC based‑layout could lead to simplify the compressor design and with a potential of capital cost reduction for peak‑operation systems in land application or size and weight reduction for propulsion purposes. So a proper optimization of the thermo‑economic performance is required.
• Application Deadline: Dec. 15, 2024 (Closed)
• Planned Start Date: March 1, 2025

Where to apply

E‑mail [e-mail]

Requirements

Research Field Engineering » Aerospace engineering Education Level Master Degree or equivalent

Research Field Engineering » Mechanical engineering Education Level Master Degree or equivalent

Research Field Engineering » Thermal engineering Education Level Master Degree or equivalent

Skills/Qualifications

Master’s degree in a relevant academic field (Mechanical, Energy or Chemical Engineering or closely related)

Specific Requirements

Candidates should possess a Master’s degree in a relevant academic field (Mechanical, Energy or Chemical Engineering, Physics, or closely related) or a degree that allows them to embark in a PhD. Additional requirements could be necessary according to specific institution’s rules.

Languages ENGLISH Level Excellent

Research Field Engineering » Aerospace engineeringEngineering » Mechanical engineeringEngineering » Thermal engineering Years of Research Experience 1 - 4

Additional Information

Salary and employment contract

• You will have an employment contract from the recruiting beneficiary. You will benefit from a competitive salary, number of days off, remote work, social security coverage. The salary will be composed of:
  • A living allowance (3400 euros per month – gross salary) this amount is then adjusted through the application of a country correction coefficient to the living allowance of the country in which the researcher is recruited. The country correction coefficients are indicated in Table 1 of the MSCA Work Programme (link )
  • Monthly mobility allowance: 600 euro/month
  • Monthly family allowance, if applicable and depending on the family situation: 660 euro/month
• Enrollment in a PhD school
• Access to state‑of‑the‑art research and supervision by recognized experts
• Participation in network‑wide training activities, workshops and conferences
• Secondments periods at other network partners’ labs

Eligibility criteria

In order to be eligible, applicants must comply with all the following rules:

• At the date of deadline, applicants must be in possession or finalizing their Master’s degree or equivalent/postgraduate degree.
• At the date of recruitment, applicants must be in possession of their Master’s degree or equivalent/postgraduate degree which would formally entitle to embark on a doctorate.
• At the date of recruitment, applicants must fulfill the transnational mobility rule: applicants must not have resided or carried out their main activity (work, studies, etc.) in the country of the recruiting beneficiary for more than 12 months in the 36 months immediately before the recruitment date – unless as part of a compulsory national service or a procedure for obtaining refugee status under the Geneva Convention.
• At the date of deadline, applicants must be in the first four years (full‑time equivalent research experience) of their research career (career breaks excluded) and not yet been awarded a doctoral degree. Career breaks refer to periods of time where the candidate was not active in research, regardless of his/her employment status (sick leave, maternity leave etc). Short stays such as holidays and/or compulsory national service are not taken into account.

Applicants must be available, full‑time, to start the program in Spring/Summer 2025 (depending on the project).

Selection process

Our selection procedure is open, transparent, merit‑based, impartial and equitable and in line with the Code of Conduct for the Recruitment of Researchers (link ).

Applicants should follow the application criteria and instructions for the position(s) that they are interested in applying for. Candidates will be informed, prior to the selection, about the recruitment process for each position and the selection criteria.

The selection procedure will consist of the following steps:

Eligibility check: The Recruitment Committee will check each application is complete and that applicants fulfil the eligibility criteria described in the previous section.

Remote Evaluation: each eligible application will be evaluated independently by the Principal Investigators of each institutions of our network, according to the DC position options expressed by the applicants.

Online interviews: the short‑listed candidates will be interviewed by a Selection Committee that will include the recruiting Principal Investigators. Selection committees will bring together diverse expertise and competences and will have an adequate gender balance.

Applications will be reviewed for eligibility and suitability based on the criteria listed for each position.

The recruiting institution will send out notification of the selection outcome after the interview. Candidates will be informed after the selection process about the strengths and weaknesses of their applications

The mail subject must begin with [DCXX] where XX is the project number (e.g. DC01 or DC13). Please include a letter of interest, a CV and at least one recommendation letter as a single pdf file (max file size 5 MB).

Applicants should send separate emails for each position for which they would like to apply.

IMPORTANT NOTE: Some host institutions require additional submission of the application documents via the host’s submission system.