| 1. |
- Grönstedt, Tomas, 1970, et al.
(author)
-
Ultra low emission technology innovations for mid-century aircraft turbine engines
- 2016
-
In: ASME Turbo EXPO 2016, Seoul, June 13-17, South Korea. - 9780791849743 ; 3:GT2016-56123
-
Conference paper (peer-reviewed)abstract
- Commercial transport fuel efficiency has improved dramatically since the early 1950s. In the coming decades the ubiquitous turbofan powered tube and wing aircraft configuration will be challenged by diminishing returns on investment with regards to fuel efficiency. From the engine perspective two routes to radically improved fuel efficiency are being explored; ultra-efficient low pressure systems and ultra-efficient core concepts. The first route is characterized by the development of geared and open rotor engine architectures but also configurations where potential synergies between engine and aircraft installations are exploited. For the second route, disruptive technologies such as intercooling, intercooling and recuperation, constant volume combustion as well as novel high temperature materials for ultra-high pressure ratio engines are being considered. This paper describes a recently launched European research effort to explore and develop synergistic combinations of radical technologies to TRL 2. The combinations are integrated into optimized engine concepts promising to deliver ultra-low emission engines. The paper discusses a structured technique to combine disruptive technologies and proposes a simple means to quantitatively screen engine concepts at an early stage of analysis. An evaluation platform for multidisciplinary optimization and scenario evaluation of radical engine concepts is outlined.
|
|
| 2. |
- King, Ulrich, et al.
(author)
-
Shape adaptive technology for aircraft engine nacelle inlets
- 2016
-
In: The Royal Aeronautical Society's 5th Aircraft Structural Design Conference.
-
Conference paper (other academic/artistic)abstract
- The ambitious emission reduction goals defined by the Advisory Council for Aviation and Innovation in Europe (ACARE), demand new technologies enabling ways to significantly improve aircraft performance. In the European Commission funded low Technology Readiness Level (TRL) project “Morphing Enabling Technologies for Propulsion System Nacelles” (MorphElle) conducted between October 2013 and November 2015, an initial investigation took place to modify the inlet of an Ultra-High Bypass Ratio turbofan nacelle with adaptive structure technology to enhance its aerodynamic performance. The goal was to be able to adopt the inlet lip to different flight conditions and therefore, increase engine performance while at the same time reducing the aerodynamic nacelle drag. A pool of concepts for an adaptive nacelle inlet was established and a down selection was performed and the most promising identified. The selected concept was further elaborated and the impact at aircraft level was examined. Designing an adaptive structure mechanism for the circular shape of a nacelle inlet has different requirements compared to an adaptive structure mechanism, for example, a flap or a slat. For a circular shape, the deformation of the adaptive mechanism in circumferential direction has to be considered as well. A structural concept was established, which consists of flexible outer skin with pneumatic tubes as actuators, which is able to handle the deformation in circumferential direction. With this mechanism it is possible to change the inlet of the used reference nacelle geometry. Numerical tools were used to perform structural and aerodynamic simulations. The results of these simulations served as input for an aircraft assessment. The inputs were nacelle weight, nacelle aerodynamic drag and thrust specific fuel consumption of the engine. With this data an aircraft model was set up and compared to two reference aircraft. The first reference aircraft is a year 2000 reference (comparable to Airbus A330-300). The second reference aircraft is similar to an Airbus A330-300 with projected Entry-Into-Service (EIS) 2025+. For the aircraft equipped with the adaptive nacelle an EIS of 2025+ was assumed as well. The results were that the adaptive nacelle showed improved values for SFC and nacelle aerodynamic drag compared to the reference nacelle geometry. Furthermore, a first prototype of the shape adaptive mechanism as proof of concept was developed.
|
|
| 3. |
- Middleton, Matthew J., et al.
(author)
-
Bright radio emission from an ultraluminous stellar-mass microquasar in M 31
- 2013
-
In: Nature. - : Springer Science and Business Media LLC. - 0028-0836 .- 1476-4687. ; 493:7431, s. 187-190
-
Journal article (peer-reviewed)abstract
- A subset of ultraluminous X-ray sources (those with luminosities of less than 10(40) erg s(-1); ref. 1) are thought to be powered by the accretion of gas onto black holes with masses of similar to 5-20M(circle dot), probably by means of an accretion disk(2,3). The X-ray and radio emission are coupled in such Galactic sources; the radio emission originates in a relativistic jet thought to be launched from the innermost regions near the black hole(4,5), with the most powerful emission occurring when the rate of infalling matter approaches a theoretical maximum (the Eddington limit). Only four such maximal sources are known in the Milky Way(6), and the absorption of soft X-rays in the interstellar medium hinders the determination of the causal sequence of events that leads to the ejection of the jet. Here we report radio and X-ray observations of a bright new X-ray source in the nearby galaxy M 31, whose peak luminosity exceeded 10(39) erg s(-1). The radio luminosity is extremely high and shows variability on a timescale of tens of minutes, arguing that the source is highly compact and powered by accretion close to the Eddington limit onto a black hole of stellar mass. Continued radio and X-ray monitoring of such sources should reveal the causal relationship between the accretion flow and the powerful jet emission.
|
|
| 4. |
- Seitz, Arne, et al.
(author)
-
Concept validation study for fuselage wake-filling propulsion integration
- 2018
-
In: 31st Congress of the International Council of the Aeronautical Sciences, ICAS 2018.
-
Conference paper (peer-reviewed)abstract
- The present paper provides an overview together with intermediate results of the work-in-progress research performed in the EC-funded Horizon 2020 collaborative project CENTRELINE (“ConcEpt validatioN sTudy foR fusElage wake-filLIng propulsioN integration”), aiming at demonstrating the proof of concept for a groundbreaking approach to synergistic propulsion-airframe integration, the so-called Propulsive Fuselage Concept (PFC). The concept features a turbo-electrically driven propulsive device integrated in the very aft-section of the fuselage, dedicated to the purpose of fuselage wake-filling. Currently at TRL 1-2, CENTRELINE's target is to mature the technological key features of the PFC to TRL 3-4. The core of the targeted proof-of-concept is formed by two experimental test campaigns supported by high-fidelity 3D numerical simulation and integrated multidisciplinary design optimisation techniques for aerodynamics, aero-structures as well as the energy and propulsion system.
|
|
| 5. |
- Seitz, Arne, et al.
(author)
-
Proof of concept study for fuselage boundary layer ingesting propulsion
- 2021
-
In: Aerospace. - : MDPI AG. - 2226-4310. ; 8:1, s. 1-65
-
Journal article (peer-reviewed)abstract
- Key results from the EU H2020 project CENTRELINE are presented. The research activities undertaken to demonstrate the proof of concept (technology readiness level-TRL 3) for the so-called propulsive fuselage concept (PFC) for fuselage wake-filling propulsion integration are discussed. The technology application case in the wide-body market segment is motivated. The developed performance bookkeeping scheme for fuselage boundary layer ingestion (BLI) propulsion integration is reviewed. The results of the 2D aerodynamic shape optimization for the bare PFC configuration are presented. Key findings from the high-fidelity aero-numerical simulation and aerodynamic validation testing, i.e., the overall aircraft wind tunnel and the BLI fan rig test campaigns, are discussed. The design results for the architectural concept, systems integration and electric machinery pre-design for the fuselage fan turbo-electric power train are summarized. The design and performance implications on the main power plants are analyzed. Conceptual design solutions for the mechanical and aerostructural integration of the BLI propulsive device are introduced. Key heuristics deduced for PFC conceptual aircraft design are presented. Assessments of fuel burn, NOx emissions, and noise are presented for the PFC aircraft and benchmarked against advanced conventional technology for an entry-into-service in 2035. The PFC design mission fuel benefit based on 2D optimized PFC aero-shaping is 4.7%.
|
|
