U.S. patent number 3,880,550 [Application Number 05/445,047] was granted by the patent office on 1975-04-29 for outer seal for first stage turbine.
This patent grant is currently assigned to The United States of America as represented by the Secretary of the Air. Invention is credited to Arthur F. Corey, Bruce E. Snyder.
United States Patent |
3,880,550 |
Corey , et al. |
April 29, 1975 |
Outer seal for first stage turbine
Abstract
An outer air seal for the first stage turbine of an engine
having the seal segments made of a high strength base material with
a highly oxidation-corrosion resistant abradable alloy layer bonded
to the surface thereof on the side adjacent the rotor blade.
Another embodiment having an abrasive layer bonded to the high
strength base material with the abradable layer being bonded to the
abrasive layer. RIGHTS OF THE GOVERNMENT The invention described
herein may be manufactured and used by or for the Government of the
United States for all governmental purposes without the payment of
any royalty.
Inventors: |
Corey; Arthur F. (Glastonbury,
CT), Snyder; Bruce E. (South Windsor, CT) |
Assignee: |
The United States of America as
represented by the Secretary of the Air (Washington,
DC)
|
Family
ID: |
23767406 |
Appl.
No.: |
05/445,047 |
Filed: |
February 22, 1974 |
Current U.S.
Class: |
415/173.4;
277/922; 277/415; 277/416 |
Current CPC
Class: |
F01D
11/12 (20130101); Y10S 277/922 (20130101) |
Current International
Class: |
F01D
11/08 (20060101); F01D 11/12 (20060101); F01d
011/00 () |
Field of
Search: |
;415/174 ;277/96 |
References Cited
[Referenced By]
U.S. Patent Documents
Primary Examiner: Smith; Robert I.
Assistant Examiner: Smith; Robert I.
Attorney, Agent or Firm: Herbert, Jr.; Harry A. Killoren;
Richard J.
Claims
We claim:
1. An outer seal for the first stage of a turbine engine,
comprising an annular seal segment support member surrounding the
blades of the first stage of the turbine engine; a plurality of
seal segments supported on the seal segment support member; said
seal segments having a layer of PWA 1045 sheet material bonded to a
high strength Nickel-Chrominum alloy base material.
2. The device as recited in claim 1 wherein the high strength base
material is PWA 663.
3. The device as recited in claim 1 wherein the high strength base
material is PWA 647.
4. The device as recited in claim 1 wherein an abrasive layer of
WS-6 is bonded to the high strength base material between the base
material and the sheet of PWA 1045.
Description
BACKGROUND OF THE INVENTION
The outer air seals for the first stage turbine of the TF30 engine
and the JT9D engine use a single material for the seal segments.
The material is selected with a compromise between strength and
corrosion resistance. In the past, abradable surfaces on the seals
have been used but these have been unsuccessful since a compound of
sufficient abradability without undesirable side effects, such as
corrosion, had not been found. Thus, abradable surfaces were
eliminated and the design returned to single material seal
segments.
BRIEF SUMMARY OF THE INVENTION
According to this invention, seal segments are provided for the
outer seal of the first stage turbine wherein a highly
oxidation-corrosion resistant abradable alloy is bonded to a strong
high temperature alloy, thus eliminating the property compromise
necessitated by the use of a single alloy. In another embodiment,
an abrasive material is bonded to the high strength material with
the highly oxidation-corrosion resistant layer being bonded to the
abrasive material.
IN THE DRAWING
FIG. 1 is a partially schematic cut away sectional view of the
first stage turbine of an engine with the outer air seal of the
invention.
FIG. 2 is an elongated sectional view of an outer air seal of the
device of FIG. 1.
FIG. 3 is an enlarged sectional view of an outer air seal for the
device of FIG. 1 according to another embodiment of the
invention.
DETAILED DESCRIPTION OF THE INVENTION
Reference is now made to FIG. 1 of the drawing which shows the
first stage rotor assembly 10 having rotor blades 12, one of which
is shown, positioned adjacent the outer air seal 14. The outer air
seal 14 has a plurality of segments 16 positioned around the rotor
assembly. The segments 16 are supported on support elements 18 and
20 on a support member 21 which are supported on the outer case 22.
All of this structure is prior art structure except the seal
14.
The seal segments 16, one of which is shown in FIG. 2, have a base
member 24 of a material PWA 647 or PWA 663 with highly
oxidation-corrosion resistant abradable layer 26 of PWA 1045
NiCrAlY diffusion bonded to the base material by heating for 1 hour
to between 1,300.degree. and 1,400.degree.F in a vacuum at a
pressure between 145 and 275 meganewtons per square meter and then
postheating two hours to between 1,900.degree. and 2,150.degree.F
at a pressure of about 15 meganewtons per square meter. Before
bonding the surfaces are cleaned by sanding and then either
chemical polishing or electropolishing. The material PWA 662, PWA
647 and PWA 1045 will be described in greater detail below.
A modification of the device of FIGS. 1 and 2 is shown in FIG. 3.
In this device, the seal segments 16 have a layer 28 of abrasive
material WS-6 bonded to the base member with the abradable layer
26' of PWA 1045 being bonded to the abrasive layer 28. This will
allow incrusion of the moving rotor blade tip into the abradable
layer until it reaches the abrasive layer whereupon some machining
of the blade tip by the abrasive layer would occur.
The composition of the materials PWA 1045, PWA 663, PWA 647 and
WS-6 are given in the following table wherein the parts by weight
given are of 100 total parts.
__________________________________________________________________________
PWA 1045 PWA 663 PWA 647 WS-6
__________________________________________________________________________
Aluminum 5.5 6.0 -- -- Bismuth -- 0.5 PPM max -- -- Boron 0.003 max
0.015 0.01 max -- Carbon 0.05 0.11 0.6 0.9 Chromium 16.00 8.0 23.4
25.0 Cobalt -- 10.0 Remainder Remainder Columbium -- 0.10 max --
1.0 Iron 0.75 max 0.35 max 1.50 max 1.0 Lead -- 10 PPM max -- --
Manganese 0.50 max 0.20 max 0.10 max -- Molybdenum -- 6.0 -- --
Nickel Remainder Remainder 10.0 15.0 Phosphorous 0.015 max -- -- --
Silicon 0.40 max 0.25 max 0.40 max -- Sulfur 0.015 max 0.015 max
0.015 max -- Tantalum -- 4.25 3.5 2.75 Titanium -- 1.0 0.2 0.9
Tungsten -- 0.10 max 7.0 7.75 Yttrium 0.2 -- -- -- Zirconium --
0.075 0.45 0.4
__________________________________________________________________________
The terms PWA 1045, PWA 663, PWA 647 and WS-6 as used in the
specification and claims will indicate the composition as given in
this table.
In some applications, other alloys than those given may be used for
the base member 24.
There is thus provided an improved outer air seal of the first
stage of a turbine engine.
* * * * *