GB2355288A - Gas turbine blade trailing edge - Google Patents
Gas turbine blade trailing edge Download PDFInfo
- Publication number
- GB2355288A GB2355288A GB9923983A GB9923983A GB2355288A GB 2355288 A GB2355288 A GB 2355288A GB 9923983 A GB9923983 A GB 9923983A GB 9923983 A GB9923983 A GB 9923983A GB 2355288 A GB2355288 A GB 2355288A
- Authority
- GB
- United Kingdom
- Prior art keywords
- trailing edge
- blade
- slot
- ceramic fibres
- turbine blade
- 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
- 239000000919 ceramic Substances 0.000 claims abstract description 30
- 239000000463 material Substances 0.000 claims description 8
- 238000000034 method Methods 0.000 claims description 7
- WAIPAZQMEIHHTJ-UHFFFAOYSA-N [Cr].[Co] Chemical compound [Cr].[Co] WAIPAZQMEIHHTJ-UHFFFAOYSA-N 0.000 claims description 2
- HBMJWWWQQXIZIP-UHFFFAOYSA-N silicon carbide Chemical compound [Si+]#[C-] HBMJWWWQQXIZIP-UHFFFAOYSA-N 0.000 claims description 2
- 229910010271 silicon carbide Inorganic materials 0.000 claims description 2
- 239000002184 metal Substances 0.000 abstract description 5
- 229910052751 metal Inorganic materials 0.000 abstract description 5
- 230000015572 biosynthetic process Effects 0.000 abstract 1
- 239000007789 gas Substances 0.000 description 9
- 150000002739 metals Chemical class 0.000 description 3
- 230000003628 erosive effect Effects 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 230000002411 adverse Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- RLQJEEJISHYWON-UHFFFAOYSA-N flonicamid Chemical compound FC(F)(F)C1=CC=NC=C1C(=O)NCC#N RLQJEEJISHYWON-UHFFFAOYSA-N 0.000 description 1
- 230000035899 viability Effects 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/141—Shape, i.e. outer, aerodynamic form
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10S415/00—Rotary kinetic fluid motors or pumps
- Y10S415/914—Device to control boundary layer
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Architecture (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Ceramic fibres 20 are inserted between the walls 24,26 of a folded metal strip 22, inserted into a slot in the trailing edge of the blade, and the trailing edge sides are squeezed to retain the strip and fibres in the slot. The fibres prevent the formation of vortices resulting from the use of a rounded trailing edge.
Description
2355288 IMPROVED TURBINE BLADE AND MANUFACTURE THEREOF The present
invention relates to a gas turbine engine turbine blade having improved gasflow shedding capability.
The present invention also relates to a Oethod of manufacturing said turbine blade.
Present day gas turbine engines operate at extremely high temperatures, eg 1400C. It follows, that the material from which the turbine blades are manufactured, must be capable of operating in those temperatures for a considerable period of time, in order to ensure commercial viability of the associated engine.
Metals which will perform satisfactorily in such temperatures have been concocted, provided they are of sufficient bulk, as to avoid erosion by the gasflow.
As is well known, the main gasflow surfaces of turbine blades are of aerofoil shape, ie they have a rounded leading edge, suction and pressure surfaces, and terminate in a trailing edge which is thin, relative to the leading portion of the aerofoil. Ideally, the trailing edge should be so thin, that the gasflows from the respective suction and pressure surfaces, on leaving the trailing edge, would flow therefrom in the form of a smooth wake. However, the need to avoid erosion dictates that the trailing edge be rounded, so much so, that the respective gasf lows break away from the trailing edge, which reduces the base pressure on the trailing edge extremity, and causes generation of a stream of vortices. This undesirable effect occurs over the full length of the blade trailing edge, and consequently adversely affects the overall operating efficiency of the associated gas turbine engine.
The present invention seeks to provide an improved gas turbine engine turbine blade.
According to the present invention, a gas turbine engine turbine blade comprises an aerofoil, from the end extremity of the trailing edge of which there projects a plurality of elongate ceramic fibres, in a direction parallel with the mean direction of gasflows which leave said trailing edge during operation of said turbine blade in an associated gas 2 turbine engine, said f ibres being arranged in side by side relationship along at least a substantial portion of said trailing edge extremity.
The present invention further provides a method of fixing a plurality of ceramic fibres into the trailing edge portion of a turbine blade so as to protrude therefrom in a direction parallel with the mean direction of gasf lows which leave said trailing edge of said turbine blade during operation in a gas turbine engine, comprising the steps of forming a slot in the blade trailing edge extremity, along at least a major portion of the trailing edge length, arranging a plurality of ceramic fibres in side by side relationship, directly or indirectly in said slot, and then squeezing the sides of said slot towards each other, so as to, directly or indirectly, trap and retain said ceramic fibres in the trailing edge portion of said turbine blade.
The invention will now be described, by way of example, and with reference to the accompany drawings, in which:
Figure 1 is a cross sectional view through a turbine blade incorporating ceramic fibres in accordance with one example of the present invention.
Figure 2 is an enlarged view of the trailing edge of the blade of Figure 1.
Figure 3 is a pictorial view of the blade of Figure 1, incorporating ceramic fibres in accordance with the present invention.
Referring to Figure 1, a turbine blade 10 has an aerofoil form, consisting of a rounded leading edge 12, a suction surface 14 1, a pressure surface 16, and rounded trailing edge 18. As can be seen in Figure 1, the blade 10 tapers in a known manner, towards the trailing edge 18, the rounded portion thereof consequently being of considerably smaller radius than the leading edge 12.
In the example being described, a plurality of ceramic fibres 20, eg silicon carbide fibres, only one of which can be seen in Figure 1, are embedded in the end extremity of the trailing edge 18, and protrude therefrom in a direction parallel with the mean direction of gasflows which leave the trailing edge 18, having passed over the respective suction 3 and pressure surf aces 14 and 16, during use of the turbine blade 10 in an operating gas turbine engine (not shown).
The ceramic fibres 20 are squeeze located in close, side by side relationship, in a slot along the length of the trailing edge 18, as is clearly seen in Figure 3, so as to provide a fibrous wall, each side of which receives a respective flow of gas from the suction and pressure surfaces 14 and 16, of blade 10.
The rounded profile of the trailing edge 18, is a radical directional departure from the profile defined by surfaces 14 and 16, and a consequence of that change is that the gasflows break away from the blade 10. However, instead of immediately developing into strings of separate vortices, as in prior art conditions, the gasflows strike respective sides of the fibrous wall 20, and are deflected thereby onto a desired flow path, as unbroken flows. There results an efficient flow of gases into the following stage of the associated turbine (not shown).
Referring to Figure 2, an alternative method of fixing the ceramic fibres 20 in the blade 10, is achieved by forming a strip 22 of appropriate width and length, from metal which is compatible with the material from which blade 10 is manufactured, and folding the strip along its length. Ceramic fibres 20 are then inserted between the resulting opposing walls 24 and 26, which are then squeezed towards each other, so as to retain the fibres 20 therein. The strip 22 is then inserted in a pre-formed slot 27 in the extremity of the trailing edge 18, and the trailing edge sides squeezed towards each other, so as to retain the strip 22 therein.. 30 Experiment has shown, that metals which are compatible with the metals from which turbine blades are manufactured, include the following: N75; NSO; and Haynes 25. Further experiment has indicated that the optimum extent of projection of the ceramic fibres 20 from the extremity of 35 trailing edge 18, is in range 1. 5 to 2. 0 times the diameter thereof. It is important, that the f it of the ceramic f ibres, or the strip 22 in their respective slots in the trailing edge 18, is such that the resulting side portions thereof do not 4 have to be moved, ie squeezed, more than 0. 50-,; of the allowed normal correction, in order to satisfactorily grip the fibres.
Claims (11)
1. A gas turbine engine turbine blade comprising an aerofoil, from the end extremity of the trailing edge of which there projects a plurality of elongate ceramic fibres, in a direction parallel with the mean direction of gasflows which leave said trailing edge during operation of said turbine blade in an associated gas turbine engine, said fibres being arranged in side by side relationship along at least a substantial portion of said trailing edge extremity.
2. A gas turbine engine turbine blade as claimed in claim 1 wherein said ceramic fibres are directly located in the material from which said blade is manufactured, via a slot formed in the length of the extremity of the trailing edge thereof.
3. A gas turbine engine turbine blade as claimed in claim 1 wherein said ceramic fibres are indirectly located in the material from which said blade is manufactured, via a folded strip of material, the ceramic fibres being arranged in said fold and said strip being located in a slot formed in the length of the extremity of said trailing edge of said blade.
4. A gas turbine engine turbine blade as claimed in any of claims 1 to 3 wherein said ceramic fibres are silicon carbide fibres.
S. A gas turbine engine turbine blade as claimed in claim 3 or claim 4 wherein the material from which said strip is made, may comprise any of the following: N75; N80 or Haynes 25.
6. A method of fixing a plurality of ceramic fibres into 30 the trailing edge portion of a gas turbine engine turbine blade so as to protrude therefrom in a direction parallel with the mean direction of gasflows which leave said trailing edge of said turbine blade during operation in a gas turbine engine, comprising the steps of forming a slot in the blade trailing edge extremity, along at least a major portion of the trailing edge length, arranging a plurality of ceramic fibres in side by side relationship, directly or indirectly in said slot, and then squeezing the sides of said slot towards each other, so as to, directly or indirectly trap and 6 retain said ceramic f ibres in the trailing edge portion of said turbine blade.
7. A method of f ixing a plurality of ceramic f ibres into the trailing edge portion of a turbine blade as claimed in claim 6, wherein said ceramic fibres are arranged directly in said slot in said trailing edge, and the sides of said slot squeezed towards each other, so as to trap and retain said ceramic fibres therein.
8. A method of fixing a plurality of ceramic fibres into 10 the trailing edge portion of a turbine blade as claimed in claim 7, including proportioning the dimensions of both slot and ceramic fibres, such that said slot sides provide sufficient grip thereon if squeezed up to 0.50-. of the normally allowed movement to correct the blade shape.
is
9. A method of fixing a plurality of ceramic fibres into the trailing edge portion of a turbine blade as claimed in claim 6, wherein a strip of material which is compatible with the material from which said blade is made, is folded along its length to form opposing walls, between which said walls said ceramic fibres are then arranged in side by side relationship, and the walls thereafter squeezed, so as to trap and retain said ceramic fibres therein, and wherein a slot is formed in the trailing edge of said blade, for the receipt and gripping of said strip, by squeezing the sides of said slot towards each other.
10. A method of fixing a plurality of ceramic fibres into the trailing edge of a turbine blade as claimed in claim 9, including proportioning the dimensions of the blade slot and folded, squeezed strip, such that said blade slot sides provide sufficient grip thereon, if squeezed up to 0.51 of the normally allowed movement to correct the blade shape.
11. A gas turbine engine turbine blade substantially as described in this specification, and with reference to the drawings.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB9923983A GB2355288B (en) | 1999-10-12 | 1999-10-12 | Improved turbine blade and manufacture thereof |
| US09/669,719 US6358013B1 (en) | 1999-10-12 | 2000-09-26 | Turbine blade and manufacture thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB9923983A GB2355288B (en) | 1999-10-12 | 1999-10-12 | Improved turbine blade and manufacture thereof |
Publications (3)
| Publication Number | Publication Date |
|---|---|
| GB9923983D0 GB9923983D0 (en) | 1999-12-15 |
| GB2355288A true GB2355288A (en) | 2001-04-18 |
| GB2355288B GB2355288B (en) | 2003-10-01 |
Family
ID=10862485
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB9923983A Expired - Fee Related GB2355288B (en) | 1999-10-12 | 1999-10-12 | Improved turbine blade and manufacture thereof |
Country Status (2)
| Country | Link |
|---|---|
| US (1) | US6358013B1 (en) |
| GB (1) | GB2355288B (en) |
Families Citing this family (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1561008A1 (en) * | 2002-11-13 | 2005-08-10 | ABB Turbo Systems AG | Slotted guide vane |
| US7901189B2 (en) | 2007-05-14 | 2011-03-08 | General Electric Company | Wind-turbine blade and method for reducing noise in wind turbine |
| US10370979B2 (en) * | 2015-11-23 | 2019-08-06 | United Technologies Corporation | Baffle for a component of a gas turbine engine |
| US10099773B2 (en) | 2015-12-18 | 2018-10-16 | Amazon Technologies, Inc. | Propeller blade leading edge serrations for improved sound control |
| US20170174321A1 (en) * | 2015-12-18 | 2017-06-22 | Amazon Technologies, Inc. | Propeller treatments for sound dampening |
| US10460717B2 (en) | 2015-12-18 | 2019-10-29 | Amazon Technologies, Inc. | Carbon nanotube transducers on propeller blades for sound control |
| US10933988B2 (en) | 2015-12-18 | 2021-03-02 | Amazon Technologies, Inc. | Propeller blade treatments for sound control |
| US10259574B2 (en) | 2015-12-18 | 2019-04-16 | Amazon Technologies, Inc. | Propeller surface area treatments for sound dampening |
| US10259562B2 (en) | 2015-12-18 | 2019-04-16 | Amazon Technologies, Inc. | Propeller blade trailing edge fringes for improved sound control |
| US10011346B2 (en) | 2015-12-18 | 2018-07-03 | Amazon Technologies, Inc. | Propeller blade indentations for improved aerodynamic performance and sound control |
| US11163302B2 (en) | 2018-09-06 | 2021-11-02 | Amazon Technologies, Inc. | Aerial vehicle propellers having variable force-torque ratios |
| US11840939B1 (en) | 2022-06-08 | 2023-12-12 | General Electric Company | Gas turbine engine with an airfoil |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB789883A (en) * | 1954-08-20 | 1958-01-29 | Power Jets Res & Dev Ltd | High speed aerofoil |
| GB1436724A (en) * | 1973-06-07 | 1976-05-26 | Bolt Beranek & Newman | Reducing sound generation in fluid-flow systems embodying foil structures |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3779338A (en) * | 1972-01-27 | 1973-12-18 | Bolt Beranek & Newman | Method of reducing sound generation in fluid flow systems embodying foil structures and the like |
| FR2602739B1 (en) * | 1986-07-28 | 1988-11-18 | Aerospatiale | BLADE OF COMPOSITE MATERIALS, WITH TWO-WELL STRUCTURE AND TWO-WAY BIRTH, AND HAVING A HONEYCOMB SANDWICH COATING, AND METHOD FOR THE PRODUCTION THEREOF |
| US4789304A (en) * | 1987-09-03 | 1988-12-06 | United Technologies Corporation | Insulated propeller blade |
| IT219392Z2 (en) * | 1990-03-12 | 1993-02-26 | FIXING SYSTEM BETWEEN EXTRUDED BUCKET WITH HOLLOW STRUCTURE FOR AXIAL FAN AND BUCKET LEG INSERTED | |
| US6139268A (en) * | 1999-03-19 | 2000-10-31 | The United States Of America As Represented By The Secretary Of The Air Force | Turbine blade having an extensible tail |
-
1999
- 1999-10-12 GB GB9923983A patent/GB2355288B/en not_active Expired - Fee Related
-
2000
- 2000-09-26 US US09/669,719 patent/US6358013B1/en not_active Expired - Lifetime
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB789883A (en) * | 1954-08-20 | 1958-01-29 | Power Jets Res & Dev Ltd | High speed aerofoil |
| GB1436724A (en) * | 1973-06-07 | 1976-05-26 | Bolt Beranek & Newman | Reducing sound generation in fluid-flow systems embodying foil structures |
Also Published As
| Publication number | Publication date |
|---|---|
| US6358013B1 (en) | 2002-03-19 |
| GB9923983D0 (en) | 1999-12-15 |
| GB2355288B (en) | 2003-10-01 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PCNP | Patent ceased through non-payment of renewal fee |
Effective date: 20111012 |