CA2603370A1 - Internal fuel manifold and fuel fairing interface - Google Patents
Internal fuel manifold and fuel fairing interface Download PDFInfo
- Publication number
- CA2603370A1 CA2603370A1 CA002603370A CA2603370A CA2603370A1 CA 2603370 A1 CA2603370 A1 CA 2603370A1 CA 002603370 A CA002603370 A CA 002603370A CA 2603370 A CA2603370 A CA 2603370A CA 2603370 A1 CA2603370 A1 CA 2603370A1
- Authority
- CA
- Canada
- Prior art keywords
- fuel
- heat shield
- proximal end
- manifold
- shoulder
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/22—Fuel supply systems
- F02C7/222—Fuel flow conduits, e.g. manifolds
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Fuel-Injection Apparatus (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
A mounting system for an annular internal fuel manifold disposed within a ga s turbine engine includes a fuel inlet assembly having a heat shield extending about a t least a portion of an inner fuel inlet tube. The heat shield has a distal end engage d with the fuel manifold and has a radially outwardly projecting shoulder proximate an opposed proximal end thereof. The proximal end of the heat shield is received within a bushing disposed within a corresponding opening of a supporting casing. The shoulder of the heat shield retains the bushing in place.
Claims (7)
1. A mounting system for an internal fuel manifold of a gas turbine engine comprising a series of supports spaced apart about the annular fuel manifold, the fuel manifold having at least one fuel conveying passage therein in fluid flow communication with a plurality of fuel injection nozzles disposed along the fuel manifold and adapted to spray fuel into the combustor, the series of supports including a fuel inlet assembly connected to the fuel manifold and providing fuel flow to the fuel conveying passage, the fuel inlet assembly having a heat shield surrounding an internal fuel inlet tube defining a fuel flow passage therein, the heat shield extending between a distal end engaged with the fuel manifold and a proximal end matingly received within an opening in a supporting fuel fairing, an annular bushing being disposed within said opening between said fuel fairing and said proximal end of the heat shield, the heat shield having a shoulder proximate said proximal end, said shoulder retaining the bushing in place within said opening of the fuel fairing.
2. The mounting system as defined in claim 1, wherein said shoulder is radially outwardly projecting from the proximal end of said heat shield.
3. The mounting system as defined in claim 2, wherein said proximal end of the heat shield defines a first diameter, said shoulder having a second diameter greater than the first diameter.
4. The mounting system as defined in claim 3, wherein said second diameter is greater than at least an inner diameter of said bushing.
5. A mounting system for an annular internal fuel manifold disposed within a gas turbine engine, the mounting system comprising at least a fuel inlet assembly having a fuel inlet tube defining therein at least one fuel flow passage in fluid flow communication with at least one fuel conveying passage within the fuel manifold, the fuel inlet assembly including a heat shield extending about at least a portion of the fuel inlet tube, the heat shield having a distal end thereof engaged with the fuel manifold and having a radially outwardly projecting shoulder proximate an opposed proximal end thereof, the proximal end being received within a bushing disposed within a corresponding opening of a supporting casing, said shoulder of the heat shield retaining the bushing in place within said opening of the supporting casing.
6. An internal fuel manifold assembly for a gas turbine engine comprising:
a fuel manifold ring having at least one fuel conveying passage therein in fluid flow communication with a plurality of fuel injection nozzles adapted for spraying fuel into a combustor of the gas turbine engine;
a mounting system for supporting and positioning the fuel manifold ring within the gas turbine engine, the mounting system including at least a fuel inlet assembly having a fuel inlet tube defining therein at least one fuel flow passage in fluid flow communication with said at least one fuel conveying passage within the fuel manifold ring, the fuel inlet assembly including a heat shield disposed outwardly from the fuel inlet tube and extending along at least a portion of a length of the fuel inlet tube, the heat shield having a distal end thereof engaged with the fuel manifold ring and having an opposed proximal end matingly received within a bushing mounted within an corresponding opening; and wherein the heat shield includes a radially outwardly projecting shoulder near said proximal end thereof, said shoulder of the heat shield abutting the bushing such as to limit relative displacement therebetween.
a fuel manifold ring having at least one fuel conveying passage therein in fluid flow communication with a plurality of fuel injection nozzles adapted for spraying fuel into a combustor of the gas turbine engine;
a mounting system for supporting and positioning the fuel manifold ring within the gas turbine engine, the mounting system including at least a fuel inlet assembly having a fuel inlet tube defining therein at least one fuel flow passage in fluid flow communication with said at least one fuel conveying passage within the fuel manifold ring, the fuel inlet assembly including a heat shield disposed outwardly from the fuel inlet tube and extending along at least a portion of a length of the fuel inlet tube, the heat shield having a distal end thereof engaged with the fuel manifold ring and having an opposed proximal end matingly received within a bushing mounted within an corresponding opening; and wherein the heat shield includes a radially outwardly projecting shoulder near said proximal end thereof, said shoulder of the heat shield abutting the bushing such as to limit relative displacement therebetween.
7. A heat shield for a fuel inlet assembly of an internal fuel manifold in a gas turbine engine, the heat shield comprising: a tubular central body portion sized such that a fuel inlet tube in receivable therein and extending between a proximal end and a distal end thereof, the distal engage being adapted for engagement with the internal fuel manifold, the proximal end having a first diameter adapted for receipt within a mating bushing of a supporting casing;
and a shoulder radially extending outwardly from at least said proximal end proximate thereto, said shoulder having a second diameter greater than said first diameter.
and a shoulder radially extending outwardly from at least said proximal end proximate thereto, said shoulder having a second diameter greater than said first diameter.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US10/764,578 US7320212B2 (en) | 2004-01-27 | 2004-01-27 | Side-fed shielded internal fuel manifold inlet tube |
| US11/534,246 | 2006-09-22 | ||
| US11/534,246 US7703286B2 (en) | 2006-09-22 | 2006-09-22 | Internal fuel manifold and fuel fairing interface |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CA2603370A1 true CA2603370A1 (en) | 2008-03-22 |
| CA2603370C CA2603370C (en) | 2011-07-26 |
Family
ID=44320363
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA2603370A Expired - Fee Related CA2603370C (en) | 2004-01-27 | 2007-09-21 | Internal fuel manifold and fuel fairing interface |
Country Status (1)
| Country | Link |
|---|---|
| CA (1) | CA2603370C (en) |
-
2007
- 2007-09-21 CA CA2603370A patent/CA2603370C/en not_active Expired - Fee Related
Also Published As
| Publication number | Publication date |
|---|---|
| CA2603370C (en) | 2011-07-26 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| EEER | Examination request | ||
| MKLA | Lapsed |
Effective date: 20220322 |
|
| MKLA | Lapsed |
Effective date: 20200921 |