Aerospace and Propulsion
i. "Technology" for gas turbine engine adjustable flow path systems designed to maintain engine stability for gas generator turbines, fan or power turbines, or propelling nozzles, as follows: 1. "Development" "technology" for deriving the functional requirements for the components that maintain engine stability; 2. "Development" or "production" "technology" for components unique to the adjustable flow path system and that maintain engine stability; 3. "Development" "technology" for the control law algorithms, including "source code", unique to the adjustable flow path system and that maintain engine stability;
| Reference | Parameter | Threshold |
|---|---|---|
| 9E003.a.1 | g (in the 001 Miller Index Direction) a stress-rupture life | > 400 hours at |
| 9E003.c.1 | ing all of the following: a. Minimum ‘cross-sectional area’ | < 045 mm |
| 9E003.c.1 | and c. ‘Incidence angle’ | < 25 o |
| 9E003.c.2 | ing all of the following: a. Minimum ‘cross-sectional area’ | < 012 mm |
| 9E003.f.3 | 8 °C)) and having all of the following: a. Injection amount | > 230 mm |
| 9E003.g | r wall lubrication and permitting operation to temperatures | > 723 K ( |
9E003.aInlet guide vanes;
9E003.bVariable pitch fans or prop-fans;
9E003.cVariable compressor vanes;
9E003.dCompressor bleed valves; or
9E003.eAdjustable flow path geometry for reverse thrust.
9E003.a.1Gas turbine blades, vanes or "tip shrouds", made from directionally solidified (DS) or single crystal (SC) alloys and having (in the 001 Miller Index Direction) a stress-rupture life exceeding 400 hours at 1 273 K (1 000 °C) at a stress of 200 MPa, based on the average property values;
9E003.a.2Combustors having any of the following:
9E003.a.2.a‘Thermally decoupled liners’ designed to operate at ‘combustor exit temperature’ exceeding 1 883 K (1 610 °C);
9E003.a.2.bNon-metallic liners;
9E003.a.2.cNon-metallic shells;
9E003.a.2.dLiners designed to operate at ‘combustor exit temperature’ exceeding 1 883 K (1 610 °C) and having holes that meet the parameters specified in 9E003.c.; or
9E003.a.2.eUtilising ‘pressure gain combustion’;
9E003.a.3Components that are any of the following:
9E003.a.3.aManufactured from organic "composite" materials designed to operate above 588 K (315 °C);
9E003.a.3.bManufactured from any of the following:
9E003.a.3.b.1Metal "matrix""composites" reinforced by any of the following:
9E003.a.3.b.1.aMaterials specified in 1C007;
9E003.a.3.b.1.b"Fibrous or filamentary materials" specified in 1C010; or
9E003.a.3.b.1.cAluminides specified in 1C002.a.; or
9E003.a.3.b.2Ceramic "matrix""composites" specified in 1C007.; or
9E003.a.3.cStators, vanes, blades, tip seals (shrouds), rotating blings, rotating blisks, or ‘splitter ducts’, that are all of the following: 1. Not specified in 9E003.a.3.a.; 2. Designed for compressors or fans; and 3. Manufactured from material specified in 1C010.e. with resins specified in 1C008;
9E003.a.4Uncooled turbine blades, vanes or "tip shrouds", designed to operate at a ‘gas path temperature’ of 1 373 K (1 100 °C) or more;
9E003.a.5Cooled turbine blades, vanes, "tip shrouds" other than those described in 9E003.a.1., designed to operate at a ‘gas path temperature’ of 1 693 K (1 420 °C) or more;
9E003.a.6Aerofoil-to-disk blade combinations using solid state joining;
9E003.a.7Not used;
9E003.a.8‘Damage tolerant’ gas turbine engine rotor components using powder metallurgy materials specified in 1C002.b.; or
9E003.a.9Not used;
9E003.a.10Not used;
9E003.a.11‘Fan blades’ having all of the following: a. 20 % or more of the total volume being one or more closed cavities containing vacuum or gas only; and b. One or more closed cavities having a volume of 5 cm^3 or larger;
9E003.b.1Wind tunnel aero-models equipped with non-intrusive sensors capable of transmitting data from the sensors to the data acquisition system; or
9E003.b.2"Composite" propeller blades or propfans, capable of absorbing more than 2 000 kW at flight speeds exceeding Mach 0,55;
9E003.c.1Having all of the following: a. Minimum ‘cross-sectional area’ less than 0,45 mm^2; b. ‘Hole shape ratio’ greater than 4,52; and c. ‘Incidence angle’ equal to or less than 25o; or
9E003.c.2Having all of the following: a. Minimum ‘cross-sectional area’ less than 0,12 mm^2; b. ‘Hole shape ratio’ greater than 5,65; and c. ‘Incidence angle’ more than 25o;
9E003.f"Technology" "required" for the "production" of specially designed components for "high output diesel engines", as follows:
9E003.f.1"Technology""required" for the "production" of engine systems having all of the following components employing ceramics materials specified in 1C007: a. Cylinder liners; b. Pistons; c. Cylinder heads; and d. One or more other components (including exhaust ports, turbochargers, valve guides, valve assemblies or insulated fuel injectors);
9E003.f.2"Technology""required" for the "production" of turbocharger systems with single-stage compressors and having all of the following: a. Operating at pressure ratios of 4:1 or higher; b. Mass flow in the range from 30 to 130 kg per minute; and c. Variable flow area capability within the compressor or turbine sections;
9E003.f.3"Technology""required" for the "production" of fuel injection systems with a specially designed multifuel (e.g., diesel or jet fuel) capability covering a viscosity range from diesel fuel (2,5 cSt at 310,8 K (37,8 °C)) down to gasoline fuel (0,5 cSt at 310,8 K (37,8 °C)) and having all of the following: a. Injection amount in excess of 230 mm3 per injection per cylinder; and b. Electronic control features specially designed for switching governor characteristics automatically depending on fuel property to provide the same torque characteristics by using the appropriate sensors;
9E003.g"Technology" "required" for the "development" or "production" of "high output diesel engines" for solid, gas phase or liquid film (or combinations thereof) cylinder wall lubrication and permitting operation to temperatures exceeding 723 K (450°C), measured on the cylinder wall at the top limit of travel of the top ring of the piston;
9E003.h"Technology" for gas turbine engine "FADEC systems" as follows:
9E003.h.1"Development""technology" for deriving the functional requirements for the components necessary for the "FADEC system" to regulate engine thrust or shaft power (e.g., feedback sensor time constants and accuracies, fuel valve slew rate);
9E003.h.2"Development" or "production""technology" for control and diagnostic components unique to the "FADEC system" and used to regulate engine thrust or shaft power;
9E003.h.3"Development""technology" for the control law algorithms, including "source code", unique to the "FADEC system" and used to regulate engine thrust or shaft power;
9E003.i"Technology" for adjustable flow path systems designed to maintain engine stability for gas generator turbines, fan or power turbines, or propelling nozzles, as follows:
9E003.i.1"Development""technology" for deriving the functional requirements for the components that maintain engine stability;
9E003.i.2"Development" or "production""technology" for components unique to the adjustable flow path system and that maintain engine stability;
9E003.i.3"Development""technology" for the control law algorithms, including "source code", unique to the adjustable flow path system and that maintain engine stability.
9E003.j"Technology""required" for the "development" of wing-folding systems designed for fixed-wing "aircraft" powered by gas turbine engines;
9E003.k"Technology", not specified in 9E003.a., 9E003.h., or 900E.3.i., "required" for the "development" of any of the following components or systems, specially designed for aero gas turbine engines to enable "aircraft" to cruise at Mach 1 or greater for more than 30 minutes:
9E003.k.1Propulsion inlet systems;
9E003.k.2Propulsion exhaust systems;
9E003.k.3"Reheat systems";
9E003.k.4"Active thermal management systems" to condition fluids used to lubricate or cool "engine rotor supports";
9E003.k.5Oil-free "engine rotor supports"; or
9E003.k.6Systems to remove heat from "compression system" core gas path flow.
Decontrol note
Les informations techniques déjà publiées ou nécessaires à l’entretien courant des moteurs (voir Note générale sur la technologie) ne sont pas soumises à contrôle.
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