US20070031260A1

US20070031260A1 - Turbine airfoil platform platypus for low buttress stress

Info

Publication number: US20070031260A1
Application number: US11/197,162
Authority: US
Inventors: Bryan Dube; Randall Butcher
Original assignee: United Technologies Corp
Current assignee: Raytheon Technologies Corp
Priority date: 2005-08-03
Filing date: 2005-08-03
Publication date: 2007-02-08
Also published as: EP1749970A2; EP1749970B1; EP1749970A3; CN1908379A; SG130114A1; TW200710319A; JP2007040295A

Abstract

A blade is provided for use in a gas turbine engine. The blade has a platform, an airfoil portion extending radially from a first side of the platform, and an attachment portion extending from a second or underside side of the platform. The attachment portion includes a buttress which abuts the second side of the platform. The blade is provided with additional material on the second side of the platform for redistributing load away from the buttress.

Description

STATEMENT OF GOVERNMENT INTEREST

The Government of the United States of America may have rights in the present invention by virtue of Contract No. F33657-99-D-2051-524 awarded by the Department of the Air Force.

BACKGROUND OF THE INVENTION

(1) Field of the Invention
The present invention relates to a turbine blade having a platform provided with additional material for reducing stress acting on the blade by distributing loads away from a buttress portion of the turbine blade.
(2) Background of the Invention
Referring now to FIGS. 1 through 3 of the drawings, there is shown a turbine blade construction used in gas turbine engines. The turbine blade 30 has a platform 32, an airfoil portion 34 (only a portion of which is shown) radially extending from the platform 32, and an attachment portion 36. The attachment portion typically includes a dovetail portion 38 for connecting the blade 30 to a rotating disk (not shown), a neck portion 40, and a buttress portion 42 which extends between the neck portion 40 and an underside 44 of the trailing edge of the platform 32. The lower speeds and temperatures faced by certain blades allow the airfoil portion to have short root necks and buttresses that adjoin to serrations. The buttress portion 42 serves to minimize secondary flow leakage. Blades which face higher stress and temperature have airfoils which use side plates to cover the leakage area between the buttress and the serrations.
Some turbine blades have a relatively large leading edge platform which is necessary to minimize flowpath leakage between the blade and vane. The large overhang of the platform, high rotor speed, short root neck, and relatively high temperature create a stress concentration where the upper serration meets the suction side and pressure side buttresses.
In order to reduce the stress on the buttress, there is needed a way to redistribute the load path away from the buttress.

SUMMARY OF THE INVENTION

A turbine blade of the present invention is provided with a system for redistributing a load path away from the buttress portion of the turbine blade.
In accordance with the present invention, a blade is provided which broadly comprises a platform, an airfoil portion extending radially from a first side of the platform, and an attachment portion extending from a second side of the platform. The attachment portion includes a buttress which abuts said second side of the platform. The blade is provided with means for redistributing loads away from the buttress.
Other details of the turbine airfoil platform platypus for low buttress stress, as well as other objects and advantages thereto, are set forth in the following detailed description and the accompanying drawings wherein like reference numerals depict like elements.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 is a side view of a portion of a prior art turbine blade;
FIG. 2 is a perspective view from the bottom of a leading edge portion of a platform and buttress used in a prior art turbine blade;
FIG. 3 is a view showing the load path in a prior art turbine blade;
FIG. 4 is a perspective view from the bottom of a turbine blade in accordance with the present invention;
FIGS. 5 and 6 are side views of a turbine blade in accordance with the present invention;
FIG. 7 is a bottom view of the turbine blade of FIGS. 4 through 6 showing the load path distribution in the turbine blade of the present invention; and
FIG. 8 is a contour map of an exemplary system for distributing the load path in a turbine blade.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENT(S)

Referring now to FIGS. 4 through 8, there is shown a portion of a turbine blade 100 in accordance with the present invention. The turbine blade 100 has a platform 102, an airfoil portion 104 radially extending from a first side 106 of the platform 102, and an attachment portion 108 extending from a second side or underside 110 of the platform 102. The attachment portion 108 includes a dovetail portion 112 for securing the turbine blade 100 in a slot (not shown) in a rotor (not shown), such as a disk. The attachment portion 108 further includes a neck portion 114 between the dovetail portion 112 and the second side 110 of the platform 102. Still further, the attachment portion 108 has a buttress 116 between the second side 110 of the platform 102 and the leading end of the neck portion 114. During operation, the buttress 116 as previously discussed is subject to stress.
The platform 102 has a leading edge 120, a suction side 122, a leading edge root face 123, and a pressure side 124. The platform leading edge 120 has a thickness T1. The suction side 122 and the pressure side 124 each have a thickness T2. The platform further has a central longitudinal axis 126.
In accordance with the present invention, the leading edge of the platform 102 is provided with additional material 140 so as to redistribute the load away from the buttress 116 towards the center of the leading edge root face 123. This additional material 140 is preferably the same material that is being used to form the platform 102 and the turbine blade 100. The additional material 140 may be formed during the casting of the turbine blade 100. In a preferred embodiment of the present invention, the additional material 140 has a shape similar to that of a platypus bill.
Referring now in particular to FIG. 8, there is shown a contour map of an exemplary additional material formation which comprises a system for redistributing the loads away from the buttress 116. The thicknesses of the additional material 140 for the various points 1-24 shown in FIG. 8 are listed in Table I. The thicknesses are given as normalized percentages with the largest thickness at the thickest point 5 being 100%.

TABLE I

PT NO.

1 2 3 4 5 6 7 8

THICKNES 41.8 53.8 70.6 93.5 100 73.5 57.1 45.3

PT NO.

9 10 11 12 13 14 15 16

THICKNESS 34.1 43.5 52.4 57.7 55.9 48.2 38.8 31.2

PT NO.

17 18 19 20 21 22 23 24

THICKNESS 30.0 34.7 38.9 40.6 38.8 34.1 30.0 27.1
The thicknesses 1-24 are taken along three lines A, B, and C in the region between the front root face 121 and the leading edge 120. Line A is located closest to the buttress 116 at a normalized distance of about 13.51% from the front root face 121. Line B is located at a normalized distance of about 47.30% from the front root face 121 and line C is located at a normalized distance of about 88.59% from the front root face 121.
As can be seen from FIG. 8, the thickness of the additional material 140 on the second side 110 gradually increases from both the suction side 122 and the pressure side 124 towards a maximum point 5 (on line A), 13 (on line B), and 21 (on line C), which maximum point is preferably offset from the central longitudinal axis 126. As can also be seen from FIG. 8, the thickness of the platform 102 on the second side 110 gradually increases from points along line C, nearest to the leading edge 120, to the point 5.
The additional material 140 is advantageous in that it distributes loads, both stress and strain, away from the buttress 116 towards the center of leading edge root face 123. This is different from conventional blades where the loads are funneled into the middle and distributed along the entire width of the leading edge of the platform.
It is apparent that there has been provided in accordance with the present invention a turbine airfoil platform platypus for low buttress stress which fully satisfies the objects, means, and advantages set forth hereinbefore. While the present invention has been described in the context of specific embodiments thereof, other alternatives, modifications, and variations will become apparent to those skilled in the art having read the foregoing description. Accordingly it is intended to embrace those alternatives, modifications, and variations which fall within the broad scope of the appended claims.

Claims

1. A blade for use in a gas turbine engine comprising:

a platform, an airfoil portion extending radially from a first side of the platform, and an attachment portion extending from a second side of the platform;

said attachment portion including a buttress which abuts said second side of the platform; and

means for redistributing load away from the buttress.

2. The blade of claim 1, wherein said platform has a suction side and a pressure side and wherein said load redistributing means comprise means for directing the load outwardly towards a center of a leading edge root face.

3. The blade of claim 1, wherein said platform has a leading edge and a thickness at said leading edge and wherein said load redistributing means includes a first region having a first thickness greater than said thickness at said leading edge and a second region having a second thickness greater than said first thickness.

4. The blade of claim 3, wherein said platform has a central longitudinal axis and said first and second regions are offset from said central longitudinal axis.

5. The blade of claim 4, wherein said first region is near the leading edge of said platform and said second region abuts said buttress.

6. The blade of claim 1, wherein said platform has a suction side with a thickness and said means for redistributing said load comprises a third region offset from a central point of said buttress and said thickness in said third region is greater than said thickness at said suction side.

7. The blade of claim 6, wherein said platform has a thickness which increases from said suction side to said third region.

8. The blade of claim 6, wherein said platform has a pressure side with a thickness and said thickness at said third region is greater than said thickness at said pressure side.

9. The blade of claim 8, wherein said thickness of said platform increases from said pressure side to said third region.

10. The blade according to claim 1, wherein said load redistributing means comprises additional material located on the second side of the platform.

11. The blade according to claim 1, wherein said second side is an underside of said platform.

12. A turbine blade comprising:

a platform having a first side, a second side, a pressure side, a suction side and a leading edge;

an airfoil portion radially extending from said first side of said platform;

an attachment portion including a neck portion extending from the second side of said platform;

a buttress positioned adjacent an intersection of said neck portion and said second side;

a system for distributing loads away from said buttress;

said distributing system comprising additional material formed on the second side of said platform.

13. The turbine blade according to claim 12, further comprising;

said additional material beginning at a first point near said leading edge and increasing in thickness to a second point abutting said buttress;

said additional material beginning at a third point adjacent said suction side and increasing in thickness from said third point to said second point; and

said additional material further beginning at a fourth point adjacent said pressure side and increasing in thickness from said fourth point to said second point.

14. The turbine blade according to claim 13, further comprising said platform having a central longitudinal axis and said second point being offset from said central longitudinal axis.

15. The turbine blade according to claim 14, wherein said first point is offset from said central longitudinal axis.

16. The turbine blade according to claim 12, wherein said airfoil portion is an overhung airfoil portion.