GB674388A - Heated intake components for gas turbine engines - Google Patents
Heated intake components for gas turbine enginesInfo
- Publication number
- GB674388A GB674388A GB8359/50A GB835950A GB674388A GB 674388 A GB674388 A GB 674388A GB 8359/50 A GB8359/50 A GB 8359/50A GB 835950 A GB835950 A GB 835950A GB 674388 A GB674388 A GB 674388A
- Authority
- GB
- United Kingdom
- Prior art keywords
- wall
- fairing
- circulation space
- gas turbine
- bullet
- 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.)
- Expired
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
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/047—Heating to prevent icing
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Supercharger (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
674,388. Gas turbine plant; axial-flow compressors. BOYD, W. April 3, 1950 [April 7, 1949], No. 8359/50. Classes 110(i) and 110(iii) A gas turbine plant has special means for distributing hot gases into an annular intake duct of the compressor. The intake of an axial flow compressor is formed between an outer fairing 25 and a nose bullet 16. The outer fairing 25 has an inner baffle wall 25a spaced by webbing 25c from :an outer wall 25b to form a circulation space 26. Hot air from any source supplied by a duct 29 to a chamber 27 passes through the circulation space 26 to an annular slot 30. A portion of the fairing 25 is bent outwardly to form a deflector 31 which guides the hot gases over the surface of the fairing. Another part of the hot gas passes through the leading edges 14 of the struts 13 into the circulation space 17 formed between an inner baffle wall 16a and an outer wall 16b of the bullet. This gas passes into the air stream through an .annular slot 20 formed between the edge .of the cap 18 and the outer wall 16b. The cap 18 is bolted to a bracket attached to the starter motor 15 and serves to hold the bullet 16 in position. If the starter is of the type requiring an exhaust outlet, this may be provided by a pipe 24 leading to the circulation space 17. .Reference has been directed by the Comptroller to Specification 653,159.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US674388XA | 1949-04-07 | 1949-04-07 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB674388A true GB674388A (en) | 1952-06-25 |
Family
ID=22075985
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB8359/50A Expired GB674388A (en) | 1949-04-07 | 1950-04-03 | Heated intake components for gas turbine engines |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB674388A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112855348A (en) * | 2021-03-12 | 2021-05-28 | 西北工业大学 | Double-wall hood anti-icing system with impact-air film structure on front edge |
-
1950
- 1950-04-03 GB GB8359/50A patent/GB674388A/en not_active Expired
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112855348A (en) * | 2021-03-12 | 2021-05-28 | 西北工业大学 | Double-wall hood anti-icing system with impact-air film structure on front edge |
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